Wide-range fuel flowmeter - DTIC · 2016-01-28 · Wide-Range Fuel Flowmeter William Seiler, Jr....
Transcript of Wide-range fuel flowmeter - DTIC · 2016-01-28 · Wide-Range Fuel Flowmeter William Seiler, Jr....
AEDC.TR.89-6
Wide-Range Fuel Flowmeter
William Seiler, Jr. Waugh Controls Corp. Chatsworth, CA 91311
July 1989
Final Report for Period June 4, 1986 - February 1988
I Approved for public release; distribution is unlimited. ]
TECHNICAL REPORTS FILE COPY
PROPERTY OF U.S. AIR FORCE AEDC TECHNICAL LIBRARY
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE BASE, TENNESSEE
AIR FORCE SYSTEMS COMMAND UNITED STATES AIR FORCE
N O T I C E S
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Qualified users may obtain copies of this report from the Defense Technical Information Center.
References to named commercial products in this report are not to be considered in any sense as an
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Technical Information Service (NTIS). At NTIS, it will be available to the general public, including foreign
nations.
APPROVAL STATEMENT
This report has b u n reviewed mad approved.
MARJORIB S. COLLIER Directmate o f T e c h n o l o ~ Deputy for Oper~om
Approved for publication:
FOR THE COMMANDER
KEITH L. KUSHMAN Technical Director Directorate of Technology Deputy for Operations
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AEDC-TR-89-6
Sa. NAME OF PERFORMING ORGANIZATION 16b.
I Waugh Controls Corporation
6~ ADDRESS (City, State, and ZlPCode)
9001 Fullbright Avenue Chatsworth, CA 91311
8a. NAME OF FUNDING/SPONSORING ISb- ORGANIZATION Arnold EngtneeringJ Development Center J
8c. ADDRESS (C/ty, State, and ZIP Code)
Air Force Systems Command Arnold Air Force Base, TN 37389-5000
11. TITLE (Include Security Clal~ification)
Wide-Range Fuel Flowmeter
OFFICE SYMBOL (tF a~/cab/e)
OFFICE SYMBOL (If applicable)
DOT
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7b. ADDRESS ( ~ , State, and ZlP Code)
9 PROCUREMENT INSTRUMENT IDENTIFICATION NUMBER
F40600-86-C0003
10 SOURCE OF FUNDING NUMBERS PROGRAM I PROJECT I TASK IWORK UNIT ELEMENT NO. ~ACCESSION NO. I No 65502F I NO.
12. P ERS.qN/U. A~J~14.qR~S) ~elLer, William Jr . , Waugh Controls Corp., Chats~rth, CA
1311. TYPE gl[: RE~ORT 113b. TIME COVERED J14 DATE OF REPORT (Year, Month, Da.y) 115. PAGE COUNT rlnam I FROM 6/4/86 TO2/3/88 , July 1989 , 117
16. SUPPLEMENTARY NOTATION
Available in Defense Technical Information Center (DTIC). ~ (Continueonmverse i f necessary and identi by block number) 17. COSATI CODES 18. SUBJECT TERMS
FIELD GROUP SUB-GROUP f l owneter Zl 05 fuel fl owmeter Zl O7 wide ran e
19. ABSTRACr (Continue on rever~ if rmcessary and identify by block number) The Phase I I Wide-Range Fuel Flowmeter (WRFF) development program is an extension of
the Phase I program completed on 26 April 1985. This program proved the v iab i l i ty of the recirculation method of wide-range flow measurement over a 140 to 1 or greater range with a l-percent or better measurement uncertainty.
The objectives of the Phase I I program were to: (1) Reduce the size of the flo~meter and electronic conditioner and provide a more functional and economically producible system; (2) Replace the recirculating pump with a smaller, more reliable unit and assure that all components tn contact with the f luid are compatible wtth jet fuels; (3) Provide means to dts- able recirculating flow when operating at high flow rates; and (4) Evaluate the performance of an air-driven pump for possible use in hazardous atmospheres.
The meter was redesigned to greatly reduce its size and weight; large and expensive man- ifolds were eliminated, and wherever possible, commercially available f i t t ings were used.
Inwardly pointing tubes were incorporated to inject and retrieve the recirculattng flow,
20. DISTRIBUTION/AVAILABILITY OF ABSTRACT I--I UNCLASSIFIED/UNLIMITED ~ ] SAME AS RPT
22=1. NAME OF RESPONSIBLE INDIVIDUAL Mr. Carlton L. Garner
DD Form 1473, JUN 86
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19. ABSTRACT. Concluded.
reducing rectrculatton f|ow variation and related recirculation flow errors. The electronic conditioner was repackaged in a standard 3-1/2- by 19-
in. rack mount. An "auto-zero" feature was created and incorporated in the electronic
conditioner, greatly simplifying and accelerating the zeroing process. Testing was conducted to verify rangeability, transient response, long-
term s tab i l i t y wtthout re-zeroing, meter performance without recirculation, and performance usin9 an air-driven pump.
UNCLASSIFIED
AEDC-TR-89-6
PREFACE
The work r e p o r t e d h e r e i n was conducted by Waugh Con t ro l s Corpora- t i o n , Chatsworth , CA, f o r the Arnold Eng inee r ing Development Center (AEDC), Ai r Force Systems Command (AFSC) under c o n t r a c t F40600-86- C003. The Air Force P r o j e c t Manager was Ms. Mar jo r i e S. C o l l i e r , AEDC/DOT, and the Waugh Cont ro l s Corp. P r o j e c t Manager was Mr. Will iam S e i l e r , J r . The r e p r o d u c i b l e s used in the r e p r o d u c t i o n of the r e p o r t were provided by the a u t h o r .
AEDC-TR-89-6
CONTENTS
Paragraph 1 1.1 1.2 1.2.1 1.2.2 2 3 3.1 3.2 3.3 3.4 3.5 3.5.1 3.5.2 4 4.1 4.2 4.3 4.4 4.5 4.6 4.6.1 4.6.2 4.7 5 5.1 5.2 5.3 5.3.1 5.4 5.5 5.6 5.7 6 6.1 6.1.1 6.1.2 6.2 6.2.1 6.2.2
INTRODUCTION Background Theory of Operation Wide Range Fuel Flowmeter Signal Conditioner
OBJECTIVES PROCEDURES
Pump Selection Recirculation Injection & Recovery WRFF Meter Design WRFF Signal Conditioner Design System Uncertainty Analysis Flowmeter Repeatability Scaler Zero Variation
TESTS PERFORMED General Mainstream Meter Calibration WRFF System Calibration Low Pressure Calibration Stability Verification Transient Response Bench Test System Test Airmotor Pump Evaluation
TESTS RESULTS General Mainstream Meter Calibration WRFF System Calibration Recirculation Flow Rate Low Pressure Calibration Stability Verification Transient Response Airmotor Pump Evaluation
CONCLUSIONS Performance Requirements Flow Range and Accuracy Transient Response Design Objectives Mechanical Electronic
1 1 1 1 3
ii 12 12 13 24 28 36 36 37 42 42 43 43 43 44 45 46 46 46 49 49 51 51 51 56 56 56 62 66 66 66 66 67 67 69
i i i
AEOC-TR-89-6
FIGURES
Figure le 2. 3. 4. 5. 6. 7. 8. 9.
I0. ii. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25.
Circulation Diagram Electronic Controller Block Diagram Logic Diagram Pump Discharge Characteristics Lateral Injection Diagram Axial Injection Diagram Calculated Recirculation Injection/Recovery Evaluation Fixture Injection~Recovery as Incorporated Photograph, WRFF WRFF Assembly 108912 Photograph, Conditioner Front Panel Photograph, Conditioner Rear Panel Assembly, Signal Conditioner 108936 WRFF Uncertainty Analysis System Calibration Curve Composite Calibration Curve Mainstream Meter Calibration Curve Recirculation Flow Rate (Curve) Low Pressure Calibration Curve Stability Calibration Curve No. 1 Stability Calibration Curve No. 2 Transient Response, Bench Test Transient Response, System Test Airmotor System Calibration Curve
2 5 8
13 15 15 23 25 25 27 29 32 33 34 41 52 53 54 55 57 58 59 63 64 65
TABLES
Table le 2. 3. 4. 5. 6.
Calculation Summary, Lateral Injection Sample Calculation, Axial Injection Calculation Summary, Axial Injection Flowmeter Repeatability Uncertainty Zero Error Analysis Summary of Tests Performed
20 21 22 39 40 50
iv
AEDC-TR-89-6
APPENDICES
APPENDIX A TEST PROCEDURE
Paragraph le i.i 1.2 2. 3. 4. 5. 6 7.
System Purge & Zero System Purge WRFF Zero WRFF Calibration WRFF Low Pressure Calibration Stability Verification Mainstream Meter Calibration Transient Response Airmotor Pump Evaluation Calibration Data Sheet No. 1 Callbration Data Sheet No. 2 Calibration Data Sheet No. 3 Calculation Sheet - % Deviation Test Equipment List System Set Up, Seraphin Flask System Set Up, Prover Calibration Calibration Curve Blank
72 72 72 72 72 73 73 74 74 75 76 77 78 79 80 81 82
APPENDIX B TEST DATA AND CALCULATIONS
Figure B,l, B.2. B.3. B.4. B.5. B.6.
Mainstream Meter Calibration System Calibration Low Pressure Calibration Stability Calibration No. i Stability Calibration No. 2 Airmotor System Calibration
84 88 93 98
103 108
AEDC-TR-89-6
1 INTRODUCTION
1.1 Background
In the testing of Jet engines, fuel flow rates must be measured
accurately over a wide range of flows, from idle to takeoff, which
may be in the ratio of 140 to 1 or greater. Further, studies of
engine performance during acceleration require that the flow meter
have excellent transient response, the acceleration time being on
the order of a few seconds. Turbine meters are ideal for measuring
flow transients, their response having been shown to be on the order
of a few milliseconds. However, limitations of rangeability (in the
order of I0 or 12 to i) have in the past demanded that two
three meters be successively switched into the stream in
cover the full range of flow rates, with the result that
required for switching results in a loss of data during
intervals and additional signal conditioning
accommodate differing calibration factors.
or even
order to
the time
critical
is required to
A Phase I Program, Contract F40600-84-C0007, was completed on April
26, 1985. This program proved the feasibility of the recirculation
method of wide range flow measurement over a 140 to 1 or greater
range with a 1.0 percent or better measurement uncertainty.
A working prototype unit was delivered under this contract.
1.2 Theory of operation, reclrculation method
1.2.1 Wide Range Fuel Flowmeter.
The Wide Range Flow Meter provides linear measurement of flow rate
over a much wider range than can b~ normally achieved by
conventional flow metering methods. Flow meters normally perform in
a linear manner only over a limited range of flow rates,
approximately 10 to 1 in the case of turbine flow meters. At rates
lower than the useable range, output is not linear and often not
AEDC-TR-89-6
repeatable. In the Wide Range Flow Meter the nonliniar region is
offset by reclrculating a stream in an additive direction through
the meter at a rate roughly equal to the minimum linear flow rate,
thus allowing the meter to operate entirely within its linear range.
Net flow rate is determined by measuring the flow rate in the
recirculating stream and subtracting this value from the value
measured by the main stream meter.
Referring to Figure I:
I FtOW ' I I
FLOW
FIGURE i. CIRCULATION DIAGRAM
The main stream turbine meter, I, is mounted in the maln stream 2.
Rec~rculating stream 4, connects downstream from the main meter and
reconnects on the upstream side. Pump 5, circulates fluid through
the reclrculating meter, 3, at a roughly constant rate of flow.
Shut off valve, 6, provides for operation of the mainstream meter
only, without reoirculation.
AEDC-TR-89-6
The two meters are readily calibrated against one another by
shutting off the main stream with only the recirculating stream
operating. The two meters are then operating at identical flow
rates, and the subtracted pulse output is set to zero by automatic
setting of a digital rate multiplier in the computing circuit. By
so doing, errors are eliminated which would result from variations
in the calibration factor of either meter, particularly when the
main stream flow rate is near zero. Such variations become iess
significant as the flow rate increases, and are negligible at the
higher rates.
It should be observed that the system calibration factor is the same
with and without recirculating flow.
With Pump 5 turned off and shut-off valve 6 closed, flow through
the mainstream meter at location 2 is identical to system flow 7.
Under these conditions the systems electronic signal conditioner is
subtracting the output of meter 3, which is zero, resulting in a
system calibration factor identical to that achieved with
recirculating flow.
1.2.2 Signal Conditioner.
The signal conditioner scales outputs from the two meters to equal
units and then subtracts the recirculating meter output to produce a
final output representing the main stream flow rate.
Referring to Figure 2, Electronic Controller block diagram, pulse
stream A is from the main stream flow meter and pulse stream B is
from the reoirculation flow meter.
The first stage is an operational
stabilize the output amplitude
increases with flow rate.
amplifier with AC feedback to
as the meter pulse frequency
AEDC-TR-89-6
The first stage output is the input to a zero crossover detector,
having an output frequency double that of its input.
The A and B pulse streams are synchronized to an internal 100EHz
clock which prevents any time coincidence between the two streams.
The 4 digit scaler multiplies pulse stream B by a factor to produce
a pulse stream B2 which is the same frequency as that from the main
stream flowmeter A when the main stream is shut off and the
recirculating stream is flowing. The B pulse stream is then sub-
tracted from the A pulse stream to produce zero frequency output at
zero main stream flow.
The subtracter Network consists of one four stage binary up/down
counter with appropriate control logic.
Any accepted B2 pulse will cause the counter to count up
and any accepted A0 pulse will cause the counter to count
pulse.
one pulse
down one
Part of the control logic senses if there is any count in the
counter. If there is, the first A0 pulse that follows any B2 pulse
will be inhibited from the A-B output. However, this same A0 pulse
will down count the counter one pulse. If, at this time, the
counter is zero and another A0 pulse occurs before another B2 pulse,
this A0 pulse is output as an A-B pulse. If a B2 pulse occurs
before another A0 pulse, the counter w111 be counted up one count
and the following A0 pulse will be inhibited from the A-B output.
Due to "on llne" variations of the pulse frequency from the A and B
pulse streams, it is possible to accumulate some extra B2 pulses.
Up to sixteen of these extra B2 pulses can be accumulated without
reducing the performance of the subtracter. These extra B2 pulses
would be accumulated if the frequency of the A0 pulse stream falls
below that frequency of Initial calibration.
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~ WAUCH CONmOLS gal IqUJlilr A~M#K - CittlmiQtlN mare1 - ~ml~ N~-mm BLOCK DIAGRAM
ELECTRONIC CONTROLLER.- WIDE RANGE FLOW METER O t'l
,:P W ?
AEDC-TR-89-6
A second part of the control logic senses when the counter is full
and, at this time, will inhibit any further count of B2 pulses.
This is to prevent a counter roll-over to zero, which would allow an
unwanted A0 pulse to be passed to the A-B output.
A two to one change in scaler resolution has been provided.
However, the increased resolution can be implemented only if the
input A and B pulse stream ratio is less than 0.5 (A/B).
If the ratio is less than 0.5, divider #I is set in the divide by
two position. This allows the A stream counter to count twice as
many pulses as compared to the divide by one charauter. However,
the B2 output would have twice as many B2 pulses as actually needed
for proper subtraction. Therefore, divider #2 must also be set in
the divide by two position. This second division of two also tends
to even the pulse to pulse period of the A-B output for better
performance of any pulse to DC converter driven by the A-B output.
The divider #3 provides an additional divide by two for the A-B
output. This will further even the pulse to pulse period of the A-B
output for smoother pulse to DC converter performance. However, the
DC converter must be scaled up by a factor of two for correct
readings.
After calibration, as product is allowed to flow, A-B pulse stream
will reflect the actual product flow. See Figure 3 for the system
logic diagram.
Automatic Scaling is performed as follows:
i. The main stream is shut off.
AEDC-TR-89-6
2. The scaling control push button PB is pressed, clearing
A and B stream counters of all counts. When PB is
released, both counters are enabled and start counting
their respective pulse streams. The B stream counter
accumulates i0,000 B stream pulses. When this count has
been reached, the scaling control disables the pulse
input of both counters.
3. The count in the A stream counter controls the
multiplication factor that is applied to the B pulse
stream so that B2 pulse stream frequency is equal to A0
pulse stream.
4. A0 and B2 pulse streams are then fed into the subtracter
network and A-B pulse stream is now zero.
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AEDC-TR-89-8
2 OBJECTIVES
The primary objective of the program was to provide a Wide Range
Fuel Flowmeter (WRFF) capable of measuring the flow of jet fuel over
a 140 to 1 or greater range with a 1.0 percent or better measurement
uncertainty and a transient response of 0.5 seconds or less.
The specified flow range of 500 to 70,000 pounds per hour, equates
(using the density of JP-4 at 60 Deg. F) to a flow rate of 1.31 to
183 gallons per minute.
Additional objectives resulting from evaluation of the prototype
WRFF created during Phase I were:
Repackage the meter to be as small and economically
producible as practical.
Replace the recirculating pump with a smaller more
reliable unit compatible with Jet fuels.
Investigate further the availability of a suitable
metering pump to replace the recirculation flow meter.
Provide means to disable the recirculating flow when not
operating in the low flow range.
Repackaged the electronic conditioner smaller and
suitable for rack or panel mounting.
Provide direct pulse outputs for both of the turbine
meters.
Investigate the performance of an air-driven pump for
possible use in hazardous environments.
11
AEDC-TR-89-6
3 PROCEDURES
3.1 Pump Selection.
Since the pump is the largest component of the WRFF and would
largely dictate the configuration of the final system, selection of
a pump was the first item addressed.
It was perceived that if a positive displacement pump could be
obtained with essentially constant flow characteristics over the
range of pressure drops anticipated, it would be possible to
eliminate the one inch recirculation flow meter. In order for a
positive displacement pump to be viable, it would have to be
competitive size and price wise with the centrifugal pump-flowmeter
combination.
It should be noted that some reservations as to reliability existed
(at least in regard to plunger type positive displacement pumps) as
a plunger pump had been evaluated during phase I and had seized
during early testing.
Manufacturers of plunger, vane, and gear type positive displacement
and centrifugal pumps were contacted.
Some of the positive displacement pump manufacturers contacted
expressed reservations about reliability in this application, and
the units ranged from 28 to 48 inches long, weighed in the
neighborhood of 200 pounds and cost from $2,100 to $2,900.
In view of the requirements for size reduction, reliability and to
produce an economically viable product, a centrifugal pump became
the obvious choice.
A Price Model SCI00-25 Centrifugal Pump was selected as being
appropriate for the application. This unit has a 316 stainless
steel head and impeller, and an explosion proof motor.
12
AEDC-TR-89-8
The pump discharge characteristics are presenteB in Figure 4,
replotted from the manufacturer's literature for clarity, and to
present pressure in PSI rather than head in feet.
12
10 ~ ~ ~ ~ - ~ ~ "~-=- :-"-'-~ "--=":':::= ":! -'-~i i=.-- =- .:i='"---- ='.'- = - "--='_'.===- -;:- i:-:: := -_:: - - .-= "-:
8 I I : --¢- I ! =I=. 1 - ................................
. . . . . . . . . . . . . . . . . . . . . . .
...................................
U.1 ~.~_ ". ".._~. ~..'. "..:" :: _--. _" ~ ~ ; ~ : ~ ~ . ~ . ] ~_ . . . . . . . . . . " 1 " - . . . . . . . . . . . . . . . . . . _ _ . . . . ~ _ o ~ . _ ~ . _ _ _ . . ~ . . . . _ . 4 .......................................... ~ t - __" ; ~ - - ~ - - -__- --__2: ~ - _ ~ - "- ~ ; - - 1 -__-.
..................................... __°. ~__;--.__
.....................................................................................
..........................................................
0 5 10 15 20 25
°
FLOW RATE (GPM)
FIGURE 4. PRICE PUMP DISCHARGE CHARACTERISTICS
The unit was also available
identical mounting provisions
our testing.
with a Gast Air Motor drive with
providing interchangeability during
- 3.2 Recirculation Injection and Recovery
During the pump investigation phase of the program it was recognized
that by injecting the recirculating flow in a downstream facing tube
and recovering the fluid in an upstream facing tube the velocity
pressure of the mainstream flow could be utilized to cancel the
mainstream pressure drop between the injection and recovery points.
13
AEDC-TR-89-6
Since the only variable in the recirculation loop is the line loss
in the mainstream flow with varying flow rates, this approach would,
if successful, result in a constant head across the pump and
essentially constant recirculation flow.
This is very desirable as it essentially eliminates any non
linearity present in the one inch recirculatlon meter as a source of
system error.
In addition, ellminatlon of high back pressures on the reclrculating
pump permit the use of a smaller, more economical unit.
Prior to fabrication of test hardware, a series of calculations were
performed to determine the magnitude of back pressures seen by the
recirculation pump with introduction and recovery of the
recirculation flow at right angles to the mainstream flow as
incorporated in the phase 1 unit, and utilizing the inwardly facing
tubes under consideration.
See Figures 5 and 6 for clarification of terms used in the following
discussion.
Three factors influence the variable pressure drop (P1 - P2) seen by
the reciroulation system as mainstream (Q2) flow rate is varied.
The primary loss is the pressure drop across the mainstream turbine
meter and associated plumbing between the introduction and retrieval
points. This pressure drop (P3 - P4) is a function of the square of
the flow rate in the metering section (Qm) which is the combined
flows (Q2) and the reolrculation flow (QI). This is the loss which
we desire to ellmlnate or greatly reduce as it is virtually zero at
low flow rates but becomes significant at higher flow rates
resulting in lower recirculatlon flow, possible reclrculation flow
meter non linearity, and operation of the reclrculation meter at a
less desirable operating point.
]4
AEDC-TR-89-6
Q2 eP3 QM
OD X .065 W.4~J..
• 065 WALL
QI,Y1 ,al Q,
eP4
FIGURE 5. LATERAL INJECTION
Q2
A:bVZ.~o ep 4
AI ,V I QU
J J 2" OD X .OtS WNJ.
1" OD X ,06S WNI
QI QI
FIGURE 6. AXIAL INJECTION
]5
AEDC-TR-89-6
The second variable to be considered is the expansion and
contraction losses incurred at the point of injection and recovery
respectlvely.
In the case of lateral injection and recovery, (Figure 5), the two
streams (Q1 & Q2) are at right angles, the injection loss is
unaffected by the mainstream velocity and the losses are
proportlonal to the velocity pressure of the one inch stream (Pvl),
and are therefore proportional to Q12.
For axial injection, (Figure 6), these losses behave quite
differently. Fcr Q2 = 0, the losses will be similar for axlal and
lateral injection. As Q2 increases the relative velocity (Vr =
VI-V2) decreases until a point is reached where V2 = Vl, the streams
merge smoothly, and the expansion and contraction losses become
zero.
In the geometry chosen, this condition occurs at a mainstream flow
rate (Q2) of 79.2 GPM.
As the mainstream flow rate increases further, V2 increasingly
exceeds Vl creating a negative relative velocity which impacts the
downstream recovery tube creating a positive pressure at P2 and has
an aspirating effect on the upstream injection tube creating a
negative pressure at P1.
The third loss contributing to the recirculation pump back pressure
is the loss within the one inch recirculation loop incorporating the
one inch flowmeter and associated plumbing. The loss incurred in
this segment will be a function of the square of the velocity (or
flow rate) in this line ~PI = K(Q1) 2.
The sum of the above losses represent the head requirement of the
recirculating pump, and in conjunction with the pump discharge
characteristics determine the recirculation flow rate.
]6
Example of calculation (Lateral injection/recovery)
Assumed
(P3 - P4) = 6.0 PSI @ Q2 = 200 GPM
Q1 = 24.0 GPM @ Q2 ~ 0
~ 62.34#/ft 3 (water at 60 deg. F)
Units
V (velocity) = FT/sec
Q (flow rate) = GPM
A (area) = in 2
Pertinent Dimensions
Recirculation tubing is 1.00 OD X .065 wall
di = .87 in
A1 = .7854 (.87) 2 = .594 in 2
Mainstream tubing is 2.00 OD X .065 wall
di = 1.87 in
A2 = .7854 (1.87) 2 - .7854 (1.00) 2 = 1.961 in 2
Equations
Pv = ~V 2
2G(144) = 62.34V 2 = .0067 V 2
(2)(32.2)(144)
AEDC-TR-89-6
V = ~ - GAL FT s mln 144 in 2 = Q(.3208)
A min in 2 7.481gai 60 sec FT 2 A
As previously cited, the back pressure (HEAD) seen by the pump (APP)
is a function of three cumulative losses:
For the calculation of P3 - P4 the flow rate through the metering
section, QM is considered to be the mainstream flow rate Q2 plus a
constant recirculation flow rate, Q1, of 24 GPM.
17
AEDC-TR-89-6
It should be observed that a minor error is introduced
adjusting Q1 for variations in recirculating flow; however,
be proven that in no case does this error exceed 0.1 PSI.
by not
it can
(P3 - P4) can be calculated for any flow rate as follows:
(P3 - P4) = (Q2 test +24) 2 X 6.0 PSI
(200 +24) 2
The expansion and contraction losses, AP exp, incurred in the
lateral mode are equal to the combined resistance coefficient K
multiplied by the veloclty pressure, Pvl, in the one inch stream.
Reference: Crane Technical Paper No. 410 (A-26)
dl = .87
d2 1.87
= .47
Resistance Coefficient (enlargement) = .62
(contraction) = .35
Combined Coefficient (K) - .97
Therefore:
AP exp = .97 PVI = (.97)(~)fvi) 2
2g (1447
Utilizing the relationship of Vl and QI,
this becomes:
AP exp = .0019 Q12
and combining constants,
The third loss contributing to the recirculation pump back pressure
is the loss within the one inch recirculatlon loop incorporating the
one inch flow meter and associated plumbing. The loss incurred in
this segment is a function of the square of the velocity (or flow
rate) in this line.
aPz = K(QZ) 2
18
AEDC-TR-89-6
The constant for this segment can be determined
(O2 = 0) condition as follows:
APP = (P3 - P4) + K(QI) 2 + AP exp.
from the no flow
Q1 assumed to be 24.0 GPM
(P3 - P4) from earlier equation = (24) 2 x 6
(224) 2
= .07 psi
AP exp = .0019 Q12 : 1.09 PSI
A Pp from Price pump curve (Figure 4) = 8.00 PSI
8.00
K
K(24) 2 + .07 + 1.09
= 8.00 - .07 - .1.09
242 .0119
We can now use the following equation to calculate recirculation
flow rate at various system flow rates.
l~Pp = (P3 - P4) + . 0 1 1 9 Q12 + .0019 O~
= (P3 - P4) + .0138 Q12
While this equation cannot be solved directly, in conjunction with
the pump discharge curve a unique solution is possible.
A value for Q1 is selected and Q~ and APp are calculated. Q1 and
P p are spotted on the pump curve. If necessary, a second value is
chosen and by interpolation a specific flow rate is obtained.
An jxample of the calculation at Q2 = 25 GPM is presented.
Q1 Q12 (P3 - P4) .0138QI 2 ~Pp
(GPM) (PSI) (PSI) (PSI)
24 5 7 6 . 2 9 7 . 9 5 8 . 2 4
2 3 . 5 5 5 2 . 2 5 . 2 9 7 . 6 2 7 . 9 1
19
AEDC-TR-89-6
Interpolation yields a reoirculatlon flow rate of 23.7 GPM at 8.02
PSI pump head.
Calculations were conducted over
GPM. Results are presented in
Figure 7, page 23.
the flow range Q2 = 0 to Q2 = 200
Table I below, and plotted on
TABLE I. CALCULATION SUMMARY, LATERAL INJECTION
Q2 Q1 App
(GPM) (GPM) (PSI)
0 24 8.00
25 23.7 8.02
50 23.3 8.10
75 22.6 8.25
i00 21.7 8.40
125 20.7 8.60
150 19.3 8.80
175 17.4 9.05
2 0 0 1 5 . 4 9 . 3 0
Calculations (Axial Injectlon/recovery)
The axial injection recirculatlon is calculated in a manner similar
to above.
The mainstream metering loss (P3 - P4) is the
lateral injection configuration explored above.
same as for the
Similarly, the loss within the one inch reclrculatlon loop is .0119
Q12 as above.
20
TABLE 2. SAMPLE CALCULATION, AXIAL INJECTION
FJ m
V2<Vl APp = (P3-P4) + .0119Q1 ~ + A P exp
AP exp. Q2 Q1 Q12 (P3-P4) .0119Q~ V2 Vl Vr Pvr (.97Pvr) APp
(GPM) (GPM) ~ (PSI) (FT/SEC) (FT/SEC) (FT/SEC) (PSI) (PSI) (PSI)
25 24 576 .29 6.85 4.09 12.96 8.87 .53 .51 7.65 24.5 600.25 .29 7.14 4.09 13.23 9.14 .56 .54 7.97 24.3 7.90 ~
Interpolation on the pump discharge curve yields a recirculation flow rate of 24.3 GPM at a head of 7.90 PSI
Q2 Q1 Q12 (P3-P4) .0119Q12 v2 Vl vl Pvr 2Pvr APp (G~} (GPM) ~PSI) (PSI) (FT/SEC) (FT/SEC) (FT/SEC) (PSI) (PSI) (PSI)
I00 24 576 1.84 6.85 16.36 12.96 -3.40 -.08 -.16 .8.53 23 529 1.84 6.30 16.36 12.42 -3.94 -.i0 -.21 7.93 23.3 8.10
Interpolation yields 23.3 GPM recirculation flow rate at 8.10 PSI.
8 9
w ? (b
AEDC-TR-89-6
However, in this configuration the entrance losses (and at higher
flow rates) the recovery obtained are not a function of Q~ alone,
and so they cannot be combined with the recirculation loop losses.
Both functions are derived from the relative velocity pressure
(Pvr) calculated from the relative velocity (Vr) which is (VI-V2).
Again, the solution was achieved iteratively using the
losses and the selected value of Q1 to obtain a fit on
discharge curve.
combined
the pump
An example of the calculations conducted above and below the flow
rate (79 GPM) where Vr = 0 are presented in Table 2.
Results of calculations from Q2 = 0 to Q2 = 200 GPM are presented in
Table 3 and graphically in Figure 7.
TABLE 3. CALCULATION SUMMARY, AXIAL INJECTION
Q2 Q1 APp
0 2 4 . 0 8 . 0 0
25 24 .3 7 . 9 0
50 24 .3 7 . 9 0
75 2 4 . 0 8 . 0 0
i 0 0 23 .3 8 . 1 0
125 23 .2 8 .18
150 23 .3 8 . 1 0
175 23 .8 8 . 0 5
200 24 .3 7 . 9 0
22
A E D C - T R - 8 9 - 6
25
(~ AXIAL INJECTION
[] LATERAL INJECTION
21 u.~ [ - .
20
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15
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1 0 0
SYSTEM FLOW RATE (GPM)
200
FIGURE 7. CALCULATED RECIRCULATION
23
AEDC-TR-89-6
A test fixture was created with inwardly facing tubes which were !,
adjustable longitudinally into tapered sections, upstream and
downstream of the mainstream flowmster to verify the theory and to
establish the correct area ratios of mainstream and recirculation
flow. See Figure 8.
These tests indicated that a I" OD X .065 Wall injection tube
entering a 2" OD X .065 Wall mainstream tube provided very nearly
optimum results.
This configuration was incorporated in the WRFF assembly.
Figure 9.
See
The theoretical benefits anticipated were confirmed during system
calibration. See paragraph 5.3.1 and Figure 19, Page 55.
3.3 WRFF Meter Design.
A layout was created providing the smallest possible envelope.
Component and assembly drawings were created, parts were fabricated,
and the unit was assembled for test.
Considerable testing was conducted with poor results due to an
incorrect and erratic scale factor being selected by the electronic
conditioner. This was at the time wrongly attributed to swirl
induced by the upstream fluid injection or variations in fluid
profile at the inlet of the meter under varying flow conditions.
A series of tests conducted with various straightening sections in
both the main stream, and recirculation loop, and perforated plate
in the main stream to produce a consistent fluid profile to the
mainstream meter did not produced satisfactory results.
It was finally determined that during the zero cycle, cavitation was
occurring in the recirculating loop suction line.
24
AEDC-TR-89-6
BOTH ENDS
I I
RECIRCULATION FLOWUETER
81 A , _ MAIN STREAM ~ SEAL FLOWMETE~
FIGURE 8. INJECTION/RECOVERY EVALUATION FIXTURE
FIGURE 9. INJECTION/RECOVERY AS INCORPORATED
25
AEDC-TR-89-6
In this device even minor cavitation can be of serious consequence
during the zero cycle since we are continuously circulating the
fluld through both meters, and the relatlvely large outputs of the
two meters are being subtracted to obtain zero.
This initial configuration had the recirculation meter
circulation shut off valve in the pump suction llne.
configuration had been chosen in an effort to create the
most desirable package.
and the
This
smallest
New hardware was fabricated and the recirculaticn
relocated downstream cf the recirculation pump with
in the overall size cf the meter.
flowmeter was
some sacrifice
A photograph cf the unit is presented as Figure i0.
As reconfigured, the unit produced repeatable data. The
straightening added: earlier was evaluated with the new
configuration.
The optimum configuration proved to be with no straightening in
either the mainstream cr recirculating lines.
This is not surprising since the downstream facing injection tube
provides symmetrical insertion of the recirculation flow end is
reasonably upstream cf the mainstream meter, and the recirculation
meter is operating at very nearly constant flow conditions.
Thq advantage of removing the straightening is that the
recirculation flow increased from approximately 20.5 GPM to 24.5 GPM
providing a zero and low flow operation in a more desirable locatlon
on the flowmeter calibration curve.
26
8,7o
13,1
FIGURE 10 . WRFF
~+AP. ~i~ ~,
m 0 ,o ==I
(p
AEDC-'rR-89-6
The assembly drawing of the unit as delivered is presented as
Figure ii.
The unit is 29.3 inches long, 13.1 inches deep, 8.7 inches high, and
weighs 82 pounds.
For comparative purposes, the unit delivered under Phase I was 31
inches long, 28 inches deep, 19.5 inches high, and weighed 148
pounds.
Referring to Figure ii, it should be noted that the union, Item 32
was added during the reconfiguration of the system to permit
utilization of the fabricated pitot assemblies, as a site for
straighteners during our investigation and as a location for a
pressure tap used during our test program. Subsequent units would
be fabricated without this item, tube assembly Item 31, and two sets
of nuts and sleeves, by elongating Item 14 to fit thus reducing cost
and weight.
3.4 WRFF Signal Conditioner Design.
The circuit design was created and a wire wrap prototype
fabricated.
board was
Initial testing was conducted utilizing slgnal generators
simulate the flowmeter input signals.
to
During early bench testing, the up/down
used to establish the system zero was
consuming.
counting technique being
found to be very time
ThE original scaling method was replaced with the 4 digit scaler and
A and B stream counters indicated in Figure 2.
28
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t4UlD
FIGURE 11. WRFF ASSY.
SEE AL108912 ~ US? ~ MA~'~IflAL~
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AEDC-TR-89-6
This approach achieves a
(recirculating) stream meter,
seconds.
zero in i0,000 pulses from the B
and required only approximately 20
Testing was conducted using an Anadex PI-608 frequency to DC
converter. This testing resulted in a revised pulse output circuit
to reduce pulse to pulse Jitter.
System testing with the flowmeter revealed that the
subtracter network did not have adequate range to
instantaneous A to B input ratio differences caused
between the two flowmeters. The circuitry was revised
the subtracter network with an up/down counter.
electronic
accept the
by phasing
to replace
All changes were incorporated, and a printed circuit board assembly
(PCBA) and enclosure were created.
Figure 12 is a photograph of the conditioner front panel. Figure 13
is a photograph of the conditioner rear panel indicating inputs and
outputs.
The individual meter inputs, amplified and doubled in frequency are
supplied to connectors at the rear of the conditioner enclosure.
See Figure 14 for the conditioner assembly drawing.
All final system testing was conducted using the final PCBA version
of the electronics.
31
m
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d
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AEDC-TR-89-6
The WRFF electrical specifications are:
Inputs:
Power input: 115 VAC at I0 watts
Input amplifiers A and B each:
amplitude: 50 mV P-P to 50 VP-P
shape: sine or square wave
frequency: 4 Hz to 4 kHz
input impedance: minimum 10 K ohm
Outputs A1 and A2:
TTL compatible: 0 to +5 volts
50 u eec wide
output current: 0.015 amp each maximum
frequency: 2 times corresponding input frequency
Output Pulse (A-B):
TTL compatible: 0 to +5 volts
output approximates a square wave
output current: 0.015 amp maximum
Recirculating Pump Control:
+5 volt at 0.025 amp maximum
output controlled by front panel ON-OFF switch
3.5 System Uncertainty Analysis.
A system analysis was conducted over a flow range of 0.5 to 180 GPM.
The possible errors evaluated stem from two sources:
Errors caused by flowmeter repeatability
Errors caused by scaler zero variation
3.5.1 Flowmeter Repeatability.
The analysis was conducted to determine the system error that could
occur as a result of ±0.02% repeatability in both the main stream
and recirculating flow~leters.
36
AEDC-TR-89-6
The recirculation flow was assumed constant at 24 GPM over the
system test range.
The uncertainty attributable to the mainstream meter was
by multiplying the flow through the meter at each flow
±0.02%. Since the recirculating meter is operating at a
flow rate of 24 GPM its contribution is 24 X .02%, or a
error of ~.0048 GPM throughout the entire flow range.
determined
rate by
constant
constant
The errors were summed, and the system error in % was calculated
based on the system flow rate.
Since the error contributed by the recirculating flow meter becomes
a significantly smaller percent of the system error at high flow
rates the error approaches that of the mainstream meter only.
See Table 4 for results.
3.5.2 Scaler Zero Variation.
The calibration factors of the two turbine flow meters used in the
WRFF have very close to a .3500 ratio.
Referring to Figure 2 and signal conditioner description 1.2.2
To provide the best possible resolution in the four digit scaler
when the meter ratios are .5000 or less divider No. 1 is in the
divide by two position. This provides an actual registration in the
scaler of .7000. To accommodate the division by two in divider No.
2 to present the proper ratio to the subtracter circuit, we will
present the ratio as .7000.
2
37
AEDC-TR-89-8
The signal conditioner processes the input signals as follows:
Fs = F2 - RFI where Fs - System output freq.
F2 = 2" meter freq. in.
F1 = I" meter freq. in.
R = Ratio = .7000
2
The recirculation flow is presumed constant at 24 GPM.
The calibration factor of the 2" meter is 474 pulses/gallon.
During electronic zero
Fs = 0
F2 = 4 7 4 ( 2 4 ) = 1 8 9 . 6 0
60
0 = 1 8 9 . 6 0 - . 7 0 0 0 F l
2
F1 = 541.71 Hz for all system flow rates
To calculate the error introduced by ~ .0001 variation in the scaler
ratio at 1.0 GPM mainstream flow:
F2 = 4 7 4 ( 2 5 ) = 1 9 7 . 5 0 Hz
6O
F s = 1 9 7 . 5 0 - . 7 0 0 0 5 4 1 . 7 1 = 7 . 9 0 1 5
2
FS at .7001 = 197.50 - .7001 541.71 = 7.8744
2 2
% Dev = (7.9015 - 7.8744) I00 = ~ .34%
7.9015
38
TABLE 4. FLOWMETERREPEATABILITY UNCERTAINTY ANALYSIS
t~b
SYSTEM FLOW RATE
(G~)
0.5
1.0
1.31
2.0
4.0
8.0
1 5 . 0
3 0 , 0
6 0 . 0
120.0
180.0
MAINSTREAM MAINSTREAM CIRCULATION TOTAL MTR FLOW MTR ERROR MTR ERROR ERROR
( G ~ ) ( G ~ ) (GPM) ( U ~ )
2 4 . 5 + , 0 0 4 9 + . 0 0 4 8 + . 0 0 9 7
2 5 . 0 + . 0 0 5 0 + . 0 0 4 8 + . 0 0 9 8
2 5 . 3 1 + . 0 0 5 1 + . 0 0 4 8 + . 0 0 9 9
26.0 + .0052 + .0048 + .0100
28.0 + .0056 + .0048 + .0104
32.0 + .0064 + .0048 + .0112
39.0 + .0078 + .0048 + .0126
54.0 + .0108 + .0048 + .0156
84.0 + .0168 + .0048 + .0216
144.0 + .0288 + .0048 + .0336
204.0 + .0408 + ,0048 + .0456
SYSTEM ERROR
+ 1.94
+ .98
+ .76
+ .50
+ .26
+ .14
+ .084
+ . 0 5 2
+ . 0 3 6 m
+ , 0 2 8 m
+ . 0 2 5
> m
9
w ? O
AEOC-TR-89-6
The error introduced by ~ .0001 scaler reading throughout the system
flow rate is presented in Table 5.
TABLE 5. ZERO ERROR ANALYSIS
SYSTEM FLOW RATE SYSTEM ERROR
a M (%)
0 . 5 + . 6 8
1 . 0 + . 3 4
1.31 + .26
2.0 + .17
4 . 0 + .09
8.0 + .04
1 5 . 0 + . 0 2 m
3 0 . 0 + . 0 1 m
60.0 < .01
120.0 < .01
180.0 < .01
I t s h o u l d b e n o t e d t h a t t h e s e e r r o r s c o u l d h e r e d u c e d b y
a d d i t i o n a l d i g i t t o t h e s c a l e r w i t h p r o p o r t i o n a l l y
t i m e .
a d d i n g a n
l o n g e r z e r o i n g
The error analysis is presented graphically in Figure 15.
40
AEDC-TR-89-6
The inner solid deviation curves represent the errors
result from ~ .02% flowmeter repeatability.
which would
The outer dashed curves represent the added error potential of a + 1
digit resolution in the electronic scaler.
For this presentation, all possible sources of error were considered
cumulative.
1 . 0 0 - - - -
.75
.50
.25
0 z o ~ .25
~ .50 a
.75
1.00 - - - -
~ - - 025
I I I 1 . 0 1 . 3 1 180
FLOWRATE (GPM)
FIGURE 15. WRFF UNCERTAINTY ANALYSIS
41
AEDC-TR-89-6
4 TESTS PERFORMED
4.1 General.
All testing was performed in accordance with Test Procedure
Appendix A.
108935,
The procedure specifies test set ups, equipment used, tests to be
performed, flow rates, calculations to be performed, and method of
presenting results obtained.
It should be noted that the system specification requires ~ 1.0%
accuracy over a flow range of 1.31 to 180 GPM. Testing was
conducted down to 0.5 GPM to ascertain system performance at lower
than specified flow rates.
Calibration data for flow rates from 0.5 GPM through 4.0 GPM were
obtained using 2.0, 5.0, and i0.0 gallon, seraphin flasks. A
start/stop button simultaneously activated a solenoid valve
controlling flow to the seraphin flasks and gated counters
collecting system pulses and the individual 2" and I" meter pulses.
A timer was also gated by the start/stop button providing run time
to better than .01 second.
Data for these runs were recorded manually at the completion of each;
test on data sheets provided. Actual test volume was adjusted using
the ± neck reading of the seraphin flasks recorded at the completion
of each run.
Testing was conducted twice at each flow rate as verification of
system repeatability.
Calibration data from 8.0 through 180 GPM were obtained using a
Waugh Controls Model 700 Microprover, This unit has a flow rate
range of 3.0 to 3,000 GPM and an accuracy of .02%. This unit with
42
p AEDC-TR-89-6
its micro processor
consecutive test runs,
counts, meter calibration factor, and test flow rate.
from the individual i" and 2" meters were gated by
processor and recorded manually at the end of the test on
sheets provided.
controller provides gates, averages two
and provides a print out of system meter
The pulses
the micro
the data
4.2 Mainstream Meter Calibration.
The system was installed in our calibration facility and the system
was purged of air. The mainstream flow was shut off downstream of
the meter and the WRFF conditioner was zeroed. The recirculation
pump was turned off and the recirculation shut off valve was closed.
Mainstream flow was initiated, and a prover calibration was
conducted from 20 to 200 GPM at 20 GPM increments.
4.3 WRFF System Calibration.
The system was purged of air and the conditioner was zeroed. A full
span calibration from 0.5 to 180 GPM was conducted. The test stand
3 HP pump was used for flow rates from 0.5 GPM through 60 GPM, and
the 40 HP pump was used for 120 and 180 GPM test points. The pump
transition point was selected to, as nearly as possible, maintain a
constant supply pressure at the WRFF. The 3 HP pump provided 58 psi
at 0.5 GPM decaying to 48 psi at 60 GPM. The 40 HP pump provided 54
psi at 120 GPM, and 46 psi at 180 GPM.
4.4 Low Pressure Calibration.
One of the program requirements was to determine
supply pressure variations on system performance.
the effects of
The system was purged and the conditioner was zeroed. A calibration
was conducted from 0.5 to 180 GPM maintaining the pressure at the
WRFF at approximately 20 psl for all flow rates.
43
AEDC-'rR-89-6
This pressure was achieved by simultaneously adjusting the test
stand throttling valve downstream of the WRFF and a test stand by
pass valve which returned pump discharge fluid directly to the test
stand reservoir.
The 20 psi pressure was selected as a result
limitations| at pressures somewhat below 20 psi,
piston would not launch and travel downstream.
of test facility
the Microprover
4.5 Stability Verification.
The object of this test was to determine the time interval over
which specified accuracy can be achieved without zero resetting.
As a result of the simplicity and short period of time required to
re-zero the system with the new auto-zero circuitry incorporated in
the Phase II unit (appr~xlmatsly 20 seconds) it was assumed that in
normal service the system would be re-zeroed prior to each test or
work shift.
Wlth this in mind, it was originally planned to conduct three
system calibratlons over a period of approximately eight hours.
However, due to longer than anticipated calibration times, and some
test stand malfunctions, a much more severe test was actually
conducted.
The malfunction referred to was in the form of "bounce" in the relay
circuit used to control the solenoid valves used for Seraphin flask
calibrations. Periodically, the valve to the seraphin flask would
see a double pulse and shut off and then reopen resulting in
overflow of the flask.
44
AEDC-TR-89-6
The system was zeroed at 3:30 P.M. on 1-20-88. The test was aborted
after three data points had been obtained due to the above mentioned
malfunction. Filterlng was added to the circuiting in an attempt to
eliminate this problem.
The test was restarted at 7:50 A.M. 1-21-88 without re-zeroing to:
1. Verify test stand performance
2. Determine whether the unit would perform satisfactorily
after being idle overnight
The test was completed satisfactorily.
At 3:55 P.M. 1-21-88, a repeat calibration was initiated.
Recurring problems with the solenoid valve controller forced
suspension of testing at approximately 5:00 P.M.
The control box providing gates to the solenoid valves and counters
was replaced with a different unit.
The test started on 3:55 P.M. 1-21-88 was resumed II:00 A.M. on
1-22-88. Testing was completed 2:05 P.M. 1-22-88.
During the period 1-20-88 through 1-22-88, the system had been
operated approximately 13 hours and forty five minutes and had been
idle in the test stand for two nights.
4.6 Transient Response.
Tests were conducted to verify that the transient
system was 0.5 seconds or less.
response of the
All transient tests utilized an Anadex PI-608 f-DC converter driving
a Sanborn Model 60-1300B strip chart recorder. The recorder was
operated at a chart speed of 100 MM/seoond to record the transient.
45
AEDC-TR-89-6
4.6.1 Bench Test.
Inltial bench tests were performed using Anadex Model FS-600
frequency synthesizers to simulate the turbine meter inputs. These
tests permitted an instantaneous change in input frequency to be
presented to the unit under test.
Bench tests were conducted on the Anadex f-DC converter only and on
the WRFF signal conditioner driving the converter. These tests,
when compared to the actual fluid calibration will indicate the
portion of the transient time attributable to the WRFF and the
Anadex f-DC converter respectively.
4.6.2 System Test.
The system was purged of air and the WRFF
zeroed using the test stand 40 HP pump.
signal conditioner was
The throttling valve was adjusted to produce 180 GPMwith the eight
inch lever operated butterfly isolation valve fully open. The
isolation valve was closed to produce 20 GPM flow. The amplitude of
the Sanborn recorder was adjusted to provide approximately 80% chart
width deflection between these two flow points.
The Sanborn recorder was adjusted to 100 MM/second and the isolation
valve was opened as rapidly as possible.
4.7 Airmotor Pump Evaluation.
An airmotor driven pump was evaluated for possible use in
for operation in hazardous areas.
the WRFF
Th? pump evaluated has the same 316 stainless steel SC I00 Price
pump head and is driven by a Gast Model 2 AM-NCC-43A air motor.
The unit requires approximately 12 SCFM at 65 psi for use in the
WRFF application.
AEDC-TR-89-6
The air motor is considerably smaller and lighter than the 1/4 HP
electric motor used, but it does of course require a well regulated
source of clean dry air. A drip oiler is required at the air
pressure inlet port. Since the injected oil is discharged with the
air at the outlet muffler, operation tends to get a little messy.
The electric motor driven pump was removed from the system, and the
air motor drive pump was installed.
Since earlier experience with this unit had indicated that the
airmotor took some time to stabilize, (RPM and flow increase with
constant air pressure) the system was operated for one half hour
prior to zeroing the system.
The system mainstream flow was shut off and the airmotor air supply
was adjusted to provide 24 to 25 GPM recirculation flow as indicated
by the recirculation flowmeter to simulate conditions produced by
the electric motor pump.
It was observed that the air pressure required to achieve the
recirculation rate desired was 82 psi which was considered extremely
high based on previous testing.
The system was zeroed, and a calibration was started. Because of
our concern with the high air pressure required, a running check of
the recirculation flow was made.
The recirculation flow increased approximately 10% and then appeared
to stabilize. At this point in time, the airmotor had been
operating approximately one hour including the preliminary half hour
"warm up"°
The test was aborted and the unit was returned to the zero flow
condition. The air pressure was readjusted, and 65 psi produced the
desired 24 GPM recirculation flow.
47
AEDC-TR-89-6
The unit was re-zeroed and a complete calibration was performed.
The air pressure was recorded at each flow rate, but was not
adjusted during the test.
48
5 TEST RESULTS
AEDC-TR-89-6
5.1 General.
All results obtained are presented in graphic form.
Test numbers were assigned to all tests conducted, and all data
sheets, calculation sheets, and graphs are identified.
Table 6 presents a summary of tests conducted.
Supporting test data and calculation sheets used to create the
curves are presented in test number sequence in Appendix B.
It will be noted by those familiar with turbine flowmeter
calibrations that the data for the individual calibration curves is
presented in a slightly unorthodox manner.
Normally, the test data would be reduced .to obtain a mean
calibration factor, and the percent deviation would be calculated as
equal plus/minus deviations about the mean factor presented. This
provides the user the most meaningful information for his purposes,
but it suffers from some shortcomings in a development program of
this nature.
Presenting mean calibration factors and + deviations results in an
accurate portrayal of the meter tested during a specific test, but
it does not provide graphic evidence of variations from test to
test. in addition, variations in underrange data obtained can
greatly influence the curve and introduce errors within the
specified operating range.
For these reasons, it was decided before testing started that
deviations would be calculated from the calibration obtained at the
maximum flow rate of the system. In addition, all system
49
TABLE 6 SUMMARY OF TESTS PERFORMED
Tests prior to 88-9 invalid because of configuration changes to the WRFF. Straightening tube bundles were removed and recirculation flow rate was increased from approximately 20 GPM to 24.5 GPM.
m
m
9 ,=
?
O
TEST NO. TEST DATE
88-9 1-14-88
88-10 1-18-88
88-11 1-18-88
1-19-88
88-12 1-19-88
88-13 1-19-88
88-14 1-19-88
88-15 1-19-88
88-16 1-20-88
88-17 1-21-88
88-18 1-21-88
88-19 1-22-88
88-20 1-22-88
88-21 1-25-88
8 8 - 2 2 1 - 2 5 - 8 8
8 8 - 2 3 1 - 2 5 - 8 8
DESCRIPTION
Mainstream Meter Calibration
Sys. Calibration - low flow
Sys. Calibration - high flow
Transient Response
Low Press. calib. - low flow
Low Press. Callb. - high flow
Stability Callb. - low flow
Stability Calib. - high flow
Stability Calib. - low flow
Stability Callb. - high flow
Airmotor Sys. Calib. - low flow
Airmotor Sys. Callb. - high flow
COMMENTS
Void-inspectlon revealed
Contaminant in 1" meter
Void-test stand relay malfunction
LOCATION - PAGE
84 54 51 73
89 52 51 72
90 52 51 72
64 56 74
94 57 56 72
95 57 56 72
99 58 56 73
100 58 56 73
104 59 56 73
105 59 56 73
V o i d - a i r m o t o r speed d r i f t
109 65 62 74
110 65 62 74
AEDC-TR-89-6
calibration deviations were calculated using the 180 GPM calibration
(474.72 pulse/gallon) of the original system calibration (Figure 16)
as 0% deviation. In this way, deviations from test to test are
graphically apparent at both the maximum and minimum flow rates.
A conventional, composite, calibration curve of all system tests
conducted is presented as Figure 17. This curve was derived from
all of the data obtained within the specified operating range of the
system. The data was reduced to obtain the mean calibration ("K")
factor and indicates a maximum deviation of ~0.55% over a range of
1.31 to 180 GPM.
5.2 Mainstream Meter Calibration. (Test No. 88-9).
The calibration curve obtained on the mainstream meter
recirculation flow shut off is presented as Figure 18.
with the
The system was linear within 0.33% from 20 to 200 GPM.
As anticipated, the recirculating flow meter output was zero for all
flow rates, and the system and mainstream meter outputs were
identical.
5.3 WRFF System Calibration. (Test No. 88-10 & -ii)
The initial system calibration is presented as Figure 16. The
maximum total deviation over the operating range is approximately
0.7%.
5.3.1 Recirculation Flow Rate
Thq data pertaining to the reclrculation flow rate was extracted
from the initial system calibration data sheets (pages 89 and 90),
and the reclrculation flow was calculated and plotted over a system
flow rate range of 0.5 to 180 GPM. See Figure 19.
51
HIDE RANGE FUEL FLOi~4ETER
SYSTEH CALIBRATION
m O ,n -.4 - n & ?
,.,.]
: > C" i-.I
, - ] i-4 o
DATE: 1-18 -88
TEST NO: 88-Io ~ 8 8 - 1 1
+2.0
+1.0
@ - I Z l . - - L d
~ I , LI
-1.0
-2.0
CALIBRATION FACTOR AT 180 GPM = 474.72 PULSES/GALLON
FLOW RATE (GALLONS PER HINUTE)
NIDE RANGE FUEL FLOWHETER
+2~0
,'z'J
+I.0
~ ,.., ~ 0
,.,)
- 1 . 0
c :
11"1
SYSTEH CALIBRATION
DATE: ~ - ~ - g 8
TEST NO:
0 eS-lo~ I1
0 e~-tg~ :.o
-2.0
FLOg RATE (GALLONS PER HINUTE)
1-18 - ~ 8
I - Z I - , ~
I - Z.Z -~.~
b-V':5. C , ~ L I 8 /~/EP~I I<.= ,q-73, o~,,
j I
: ! !
!
I
~T I
i I I
lli
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i -1 1 Z
1, " !
I11 0 ."7 - I :p go .,,p
MIDE RANGE FUEL FLOI,~ETER
HAINSTREAH HEXER CALIBRATION
DATE: I - 1 4 - 88
TEST NO. , ~ 8 -
CALIBRATION FACTOR AT 200 GPM : 474 .66 PULSES/GALLON
m 0 9 -4
W ? C~
r r l
m
Z ~ •
0 ; - " Z
+1.0
0
.,1.0
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~ j ~ ! ~ j ~ i ~ i ~ N ~ I ~ i ~ ` ~ i i ~ j ~ ~ d ~ i l!l!lllltll ~I~i~jH~jId.J!i~i~i~'j~jij~Hi~!i~iHi!N~iH~ii~!j~!~``Ij~i~i~Hi~i~ IIIIIIt~l!ltl!lll!lllilllllltlllllilt!l]lllJllllitlllllllllll!i!ll!ll!llH!lli I J ~ 1 l ~lllllJltlll!!llllllltt!iiililllllll]liillli!tllllliltlllllllllllllllilll i j lilJtllll!lli!lilltlltllllll I~tll!lIlId!~lJl!!l!tlllllllllll!lll~ll!!!ll!l!!l!!!!lll! Illii iilll '111 jl!ll Itllllll~llllli ~i~i~i~ii~"h~i~I~"d~!~j~i~ii~i~i~j~ii~i~iij~i~!i~jjI~j~ Whii:lJ,lllil~i,l,lih,lill!liiiilit!llillJl;l!iliii,,hii!hiHh,ih,' hlllli,lllhl I!lllilllillllll Ill I Il l l l liil l l l l l l l l I ~I d ltlilllllll~llllllllllll]llllllitllllllllllllllllll 0 20 40 60 80 100 1
FLOkl RATE
(GALLONS PER HINUTE)
l l i l l l l l l l l l l l l l l l l l i i l l~ llIllll!!lllllllililillll!~lllillll
t llllJ~llltl!!lllllillllllllllll H/llll!lliiili:lll!il!liilllllltl lllllllllllllillli!llllllil~lllllll iJ!iliiiiliiilliJiiliiiili,!lil!il lillli!lll~ll~llii!l~il,lJilill!Jil
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IIIIIIIIIIIIIIIMIIIIHIIIIIIIIIIIIIIIII IIIIIIIIIHIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIII IIIlUlUlIIIIIIIMMIIIIlUlIIIIII IIIIIIIIIIIIIIHIIIIIIIIIIIIIIIIIIIIIIIIIII IIIMIHMIIIIIIIIIIIIIIIIIIIIII IllfllllBWlfllllillllllllmlllfl IImMIIIlllllilllUUllllllllllmll ~,lllllllllllllXUill.lllllllllllUlllllll Iillllllllllllllllllliilllllllllllllllllii IIlIIIIIlBIIIIIIIIIlIIIIIIlUMHI IIIIIIIIIIIIII!111111111111111111111111111 IIIIIIIIIIIIIIilIIIIHIIIIIIIIIIIIIIIIIIII IIIIIIIUIIIIIUIIIIIlUlIIlUlIIIIIIIIIII I I Imllf l l lMIl l l l l~ltHfl l f l f l
I l l f l lBIll lt l l lNIMlll lf lf l lf lf l !IIIIIIIIIIIIII~IIlIIIIHIIlIIUII'
;~ l:I, '~ol
~n
S¥S. FLOW (GPM)
0.5 1.0 2.0 4.0 8.~
15.0 30.0 60.0
120.0 180.0
1 I~ METER PULSES
138333 177036 157991 81119 97069 50403 27185 13750 6892 4926
TIME
248.68 318.41 284.16 146.07 174.728 90.454 48.637 24.435 12.055 8.268
1" METER FREQ RECIRC. FLOW (HZ) (GPM)
556.27 24.65 NOTE: Meter Pulses and time 556.00 24.64 extracted from Figure B.2. 555.99 24.64 Pages 89 & 90 555.34 24.61 555.54 24.62 557.22 24.69 i" Meter Calib. Factor 558.94 24.77 is 1354 Pulses/Gal. 562.72 24.94 571.71 25.33 Flow (GPM) = f(Hz}60 595.79 26.40 calib.Factor
E-
z
o
27
25
24
I I, , ltllH!l!hl !
li!lllill'~ll]!!lit!illiilli!llltii! ,;,,~ ~~t!! l l l t ! l t l l l i!!i!!!~
0,5 1 . 0
III
iii !!!! I_1!1 ,31
I]~I~[]IH~,IIIIIIIIItlIH~IIIIIIIIIIIIIilItlI!tIItf fti l ill I I~ l l l l l l t I t l l lllilllfllllll!lHilltl!!lltlltlllllll',lltiillllllllllllllllllllllfllllttl!ilt! H~ I I I I I f i l ial NNI II HdNHI]I I 111 IIlll it l]lll!!llllltlltfiiltllfliltlllilllllJtllllllllltl]tfll ;1~t I,I~:HI It!lll',lltlli!zliililflllll]lllllllllillllit~l!llll t l l l I It ~llll t [1 ~ t l l ~ H I l l ~llllJlllllll,flHi~ltlllll~lll'ltlllll~tll!l:l I I I t l l I I I l l L " li[ll]l]]lJII]t I l L I I I I I 1 .1
' ": i " ' ' l l l I . J I I l l l l l l
lO lO0
FLOg RATE (GALLONS PER HINUTE) >
m
n
o0 &
.6,EDC-TR-89-6
It is interesting to observe that the actual recirculation flow
rates achieved are constant over a system flow rate cf 0.5 to i0
GPM. This is the critical operating range of the WRFF as it is the
range in which the recirculation meter non-repeatability or
linearity produce substantial system errors which become
insignificant at higher flow rates.
The injection and recovery means employed have actually induced a
slight recirculation flow rate increase at higher system flows.
5.4 Low Pressure Calibration. (Test No. 88-12 & -13)
The calibration curve obtained with a constant 20 psi system
pressure is presented as Figure 20. The maximum total diviation
over the operating range is approximately 0.5%.
5.5 Stability Verification. (Test No. 88-17 through 88-20)
The first calibration conducted to verify long term stability is
presented as Figure 21. At the time this calibration was completed,
the system had been in operation for a period of approximately 9
hours and 30 minutes, and had been sitting idle in the test stand
overnight since it had been zeroed at 3:30 P.M. on 1-20-88. At this
time, the maximum total diviation over the flow range of 1.3 to 180
GPMwas approximately 0.7%.
The final stability calibration is presented as Figure 22. At this
time the system had accumulated approximately 13 hours and forty
five minutes and had been idle twice overnight since it was
originally zeroed.
5.6 Transient Response.
Figure 23 presents the results of bench tests conducted on the
electronics and an Anadex f-DO converter indicating the
electronics by itself has a virtually zero time constant.
WRFF
WRFF
The tests were conducted using Anadex Model FS-600 Frequency
Synthesizers driving the Anadex converter or the WRFF electronics.
56
WIDE RANGE FUEL FLObI4ETER
SYSTEH CALIBRATION
DATE: 1-19-88
TEST NO: B8-17.. ~ 8•-13
+2.0
-zl
+1.0 r n
C~
~,,m Z
~.~ o L'11
~ - 1 . 0
U
- 2 . 0 0 . 5
It11! lill
I Ill]
im | l
"/~kl
i i i ! ! !
i i i
iii- 1.0
1 131
CALIBRATION FACTOR AT 1 8 0 GPM = 4 7 4 . 6 2 P U L S E S / G A L L O N
10
FLOH RATE (GALLONS PER MINUTE)
100
f11 C~
- I ,:p ~o ?
MIDE RANGE FUEL FLOi~ETER
SYSTEH CALIBRATION
9 - - i ,.p (10 ?
DATE: I - ~.1- 8 8
TEST NO: 8e , -17 ~ 88-18, CALIBRATION FACTOR AT 180 GPM = 474.64 PULSES/GALLON
Go
t-n
+2.0
+1.0
,cn . - ]
b.~ 0 1 " - -
~__.~. o : : ~ I.aJ
p~ N 5
~ -1.0 Z 0
-2.0 100
I-I |.1
ii I ]
t t
T! .1 I iJ , ,
i:i |1 f~l
- t 1 .H :I:1
tt tl
FLOW RATE (GALLONS PER NINUTE)
WIDE RANGE FUEL FLOMHETER
SYSTEH CALIBRATION
DATE: I-2-2--88
TEST NO: 8 8 - 1 9 , ~ 8 B - 2 o CALIBRATION FACTOR AT 180 GPH = 474 .44 PULSES/GALLON
~ q
t..n
t ~ ~ o
+2.0
+I .0
==, e,-i C-~ Z ,"-- .
OF-- I--- ' "
~ ~ 0
~ -1.0 Z 0
t ~
-2.0
FLOW RATE (GALLONS PER MINUTE)
0 .-I ,.p ?
AEDC-TR-89-6
The Anadex output was recorded on a Sanborn Model 60-1300B strip
chart recorder at a paper speed of i00 MM per second.
The chart of Figure 23A presents the output of the~nadex converter
alone, while the chart of Figure 23B indicates the transient
response output of the Anadex converter driven by the WRFF
electronics subjected to an instantaneous frequency change.
The transients were created by flipping a toggle
input frequencies, and no significance can be
spacing of the transients shown.
switch to switch
attributed to the
These tests were conducted using range 5 of the Anadex converter set
for a full scale frequency of 1,600 Hz.
All tests were conducted with worst possible conditions for ripple
and to achieve the best possible transient responseT WRFF " T I" and
Anadex "High" transient response setting.
Some explanation of the functioning of the WRFF electronics is
required for clearer understanding of the frequencies used in these
tests.
The frequencies in all cases were selected as typical of those
observed during system testing.
Thus, the frequencies of 1422 and 158 Hz at 180 and 20 GPM of chart
Figure 23A are representative of the WRFF system output with a
calibration factor of 474 pulses/gallon.
60
AEDC-TR-89-6
The WRFF electronics operates by subtracting the reoirculating flow
from the flow seen by the mainstream meter. To compensate for the
different calibration factors of the two flowmeters, a four digit
"scaler" is selected during the zero cycle and is applied to the
recirculating meter output. This scaler is merely the ratio of the
meter outputs at a given flow rate, and a typical value is .3459.
Thus: fs = f2-R (fl)
Where fs = system frequency output
f2 = frequency of the mainstream (2") meter
fl = frequency of the recirculating (i") meter
R = scaler = f2 = .3459
fl
The input frequencies to be applied to the WRFF electronlcs for the
test of Figure 23B were determined as follows:
Referring to Figure 23B at 20 GPM:
f2 input is to be determined
fs output is 158 Hz
fl = 482 Hz (typical of 21.1 GPM reclroulatlon)
R = .3459
fs = f2 - R(fl)
f2 - fs + R(fl} = 158 + .3459 (482) = 324.7 Hz
At 180 GPM:
fs = 1422 Hz
f2 = 1422 + .3459 (482) = 1 5 8 8 . 7 H z
61
AEDC-TR-89-6
It can be seen that the outputs created by the WRFF
from the two flowmeter inputs are exactly the same as
the single signal generater in Figure 23A after proper
of the recirculation flow signal.
conditioner
provided by
eubtraction
Figure 24 presents the results of an actual system hydraulic
transient test.
The response time of the system to 63% of the step change provided
is approximately 100 milliseconds. This includes the time required
to manually open the butterfly valve and overcome the fluid inertia
of the test facility, and the time constant of the Anadex frequency
to DC converter.
5.7 Airmotor Pump Evaluation. (Test No. 88-22 & -23)
The results of a system calibration using a Gast airmotor driven
pump to provide recirculation flow are presented as Figure 25. The
deviation of the airmotor driven system over a flow range of 1.3 to
180 GPM was approximately 0.75%.
62
AEDC-TR-89-6
I I . . . . . . . . . . . . i
I I
FIGURE 23. TRANSIENT RESPONSE, BENCH TESTS
6 3
AEDC-TR-89-6
FIGURE 24, TRANSIENT RESPONSE, SYSTEM TEST
64
WIDE RANGE FUEL FLOkI4ETER
SYSTEM CALIBRATION
DATE: 1 - 2 5 - B 8
TEST NO: 88-2..2- y ~ 8 8 - Z 3
+2.0
CALIBRATION FACTOR AT 1 8 0 ( ; P M = 4 7 4 . 2 8 PULSES/GALLON
.'rJ
L"rJ
r./1 +1.0
pO
Q ¢~, I,-- • ,,-G Z
~ 0 N e t " O~ ~=" Z.=.l
r.~ ' e " v
~ - 1 . 0
,.-!
Z
-2.0
FLOW RATE (GALLONS PER MINUTE)
( • D I S C H A R G E MUFFLER. DEFROSTED BEFORE 2 GPM RUN.
m
oD ? O~
AED~TR-8~6
6. CONCLUSIONS
The WRFF Contract Statement of Work called out certain specific
performance requirements, design objectives, and tests to be per-
formed.
These requirements were all satisfied as indicated below.
6.1 Performance Requirements
6.1.1 Flow Range and Accuracy
The WRFF was to be capable of measuring the flow rate of aviation
fuels over a flow range of 140 to 1 (1.31 to 183 GPM) with a 1.0% or
better measurement uncertainty.
The composite calibration curve (Figure 17, page 53) covering all
system tests conducted with the electric motor driven pump indicate
that the unit is capable of providing flow measurement with an
accuracy of ~ 0.55% over the flow range of 1.31 to 183 GPM.
It should be noted that the testing conducted during this period
represents approximately 24 hours and 15 minutes including one
period (stability tests No. 88-17 through 88-20) during which the
system accumulated approximately 13 hours and 45 minutes and had
been idle twice overnight since it was originally zeroed verifying
good long term system stability.
6.1.2 Transient Response.
The statement of work specified that the system must be
measuring flow transients with a response time of 0.5
less.
c a p a b l e o f
s e c o n d s o r
As indicated in Figure 24, page 64, the time constant of the system
(including the response of an Anadex PI-608 f-DO converter used to
drive the Sanborn strip chart recorder and the time required to open
an 8 inch manual butterfly valve) proved to be approximately 100
msec with a step change in flow rate from 20 to 180 GPM.
AED~TR-8~6
6.2 Design Objectives.
The design objective of the Phase II program was to bring the system
produced in the SBIR Phase I effort into a more producible form, as
follows:
(1)
(2)
(3)
6.2.1 Mechanical
Package the meter as small as practical.
The unit was repackaged as indicated in Figure 10, page 27.
The resulting unit is 29.3 inches long, 13.1 inches deep,
8.7 inches high, and weighs 82 pounds.
This represents a considerable reduction over the unit
delivered under Phase I which was 31 inches long, 28 inches
deep, 19.5 inches high, and weighed 148 pounds.
Replace the recirculatlon pump with a smaller,
reliable unit compatible with Jet fuels.
more
The price centrifugal pump selected is of all stainless
steel construction. This unit is the smallest unit that
will provide the recirculation flow required, and should
prove extremely reliable.
Investigate further the availability of a suitable metering
pump to replace the reclrculatlon flow meter.
As indicated in paragraph 3.1, page 12, manufacturers of
plunger, vane, and gear type metering pumps were contacted.
The combination of a centrlfugal pump and recirculation
flow meter proved to be superior to a metering pump in
cost, size, weight and percelved reliability.
67
AEDC-TR-89-6
(4) Provide means to disable the recirculating flow when not
operating in the low flow range.
A shut off valve, item 9,
incorporated to provide a
reoirculation flow.
of Figure ii, page 29 was
means of shutting off the
The conditioner was zeroed, and the system was calibrated
without reoirculating flow. The calibration curve obtained
is presented as Figure 18, page 54.
The calibration factor (474.66 Pulses/Gallon) obtained at
200 GPM is within .013% of that obtained for the initial
system calibration presented as Figure 16, page 52.
The unit was linear within 0.33% from 200 GPM to 20 GPM.
(5) Investigate the advantages/disadvantages of an air-driven
pump.
The air motor driven pump proved to be an acceptable
alternative for use in hazardous areas. The motor took
from one half to one hour to stabilize at a given air
pressure. Once stabilized however the system provides a
calibration with a maximum excursion of 0.9% from 1.31 to
180 GPM (Figure 25, page 65).
(6) Investigate the effects of supply pressure variations.
A system calibration was performed over a flow range of 0.5
to 180 GPM maintaining the pressure at the WRFF at
approximately 20 psi for all flow rates. See Figure 20,
page 57 for results.
68
AEDC-TR-89-6
The calibration factor (474.62 Pulses/Gallon) at 180 GPM is
within .02% of that obtained for the initial system
calibration of Figure 16, page 52.
The calibration curve from 2.0 to 180 GPM exhibited only
approximately 0.35% non llnearity and was very similar to
the Initlal system callbratlon from approximately 2.0 to
180 GPM.
( l )
Under range data obtained at 0.5 and 1.0 GPM indicate
better performance than obtained on the initial system
calibration; however, as indicated in Figure 15, page 41,
data at these extreme flow rates is subject to considerable
uncertainty, and the difference may more logically be
attributed to small variations in flow meter repeatability
or zeroing than line pressure variations.
6 . 2 . 2 Electronic
Repackage the electronic equipment into a more compact size
suitable for rack or panel mounting.
The WRFF slectronlc conditioner has been repackaged in a
standard 19 x 3.5 inch rack configuration (Figure 12, page
32).
(2) Provide direct pulse outputs from each meter.
Figure 13, page 33, presents the conditioner rear
configuration indicating the individual A and B flow
output connectors.
panel
meter
The output signals provided are TTL compatible 0 tc +5 volt
50 M second wide pulses at twice the flow meter input
frequency.
69
AEDC-TR-89-6
APPENDIX A
TEST PROCEDURE
WIDE RANGE FUEL FLO~[ETER
71
AEDC-TR-89-8
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
1.0
2.0
3.0
SYSTEM PURGE & ZERO
i.I System, Purge
Open test stand valves and flood system. Open Butterball valve and turn on WRFF reclrculating pump. Turn on test stand 3HP pump and establish approximately 60 GPM. Bleed all air from prover end test stand.
1 . 2 WRFF Z e r o
Close isolation valve downstream of WRFF to eliminate mainstream flow. Press "calibrate" push button on WRFF electronics to z e r o .
WRFF CALIBRATION
Perform calibration from 0.5 to 180 GPMmalnstream flow rate, recording all data Indicated on calibration data sheets I & 2.
F l o w r a t e s 0 . 5 t h r o u g h 60 GPM t o b e r u n u s i n g 3HP pump . 120 & 180 GPM t o b e c o n d u c t e d u s i n g 40 HP pump.
C a l c u l a t e % d e v i a t i o n a s i n d i c a t e d o n " C a l c u l a t i o n S h e e t - %
D e v i a t i o n " .
WRFF LOW PRESSURE CALIBRATION
Conduct calibration from 0.5 to 180 GPMmainstream flow rate using 3 HP pump for flow rates 0.5 through 60 GPM and 40 HP pump for 120 and 180 GPM. Adjust stand by-paus valve to obtain approximately 20 PSI at WRFF at each flow rate.
R e c o r d a l l d a t a i n d i c a t e d o n c a l i b r a t i o n d a t a s h e e t s 1 & 2 .
Calculate % deviation.
Note: For this test calculate t deviation using K (180) from 2.0 as zero deviation.
Upon completion of this test establish approximately i00 GPM mainstream flow using 3 HP pump and let run.
Date 12/01/87 1 /8 /88 72 1 0 8 9 3 5 Page 1 o f 11
AEOC-TR-89-8
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
4.0
5.0
8TABILITYVERIFICATION
4.1 Four Hours
Four hours after performing the calibration of 2.0 above, repeat calibration.
Calculate % deviation.
Note: For thl8 test calculate % deviation using K (180) from 2.0 as zero deviation.
Upon completion of thl8 test establish approximately i00 GPM mainstream flow using 3 HP pump and let run.
4.2 Seven Hours
Seven hours after performing the calibration of Z.0 above, repeat 4.1.
Shut down system.
MAINSTREAM METER CALIBRATION
5.1 Purge & Zero per 1.0
5.2 Turn off WRFF recirculatlng pump and close Butterball valve.
5.3 Conduct callbration from 20 to 200 GPM recording all data indicated on data sheet 3.
Flow rates 20 through i00 GPM to be run with 3 HP pump. 120 through 200 GPM to be run using 40 HP pump.
Calculate % deviation as indicated on data sheet.
Note: For this test P1 will be zero or essentially zero. P2 will equal PS.
D a t e 1 2 / 0 1 / 8 7 1/8/88
73 108935 Page 2 of ii
AEDC~TI~8~6
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
6.0
7.0
TRANSIENT RESPONSE
C o n n e c t o u t p u t o f WRFF e l e c t r o n i c s t o A n a d e x Mode l P I - 6 0 8 AC/DC c o n v e r t e r . C o n n e c t o u t p u t o f c o n v e r t e r t o S a n b o r n M o d e l 60-1300B strip chart recorder.
Purge & Zero system par 1.0
Using 40 HP pump, adjust throttling valve to produce iS0 GPM with isolation valve fully open. Close isolation valve to produce 20 GPM flow.
A d j u s t a m p l i t u d e o f S a n b o r n t o p r o v i d e a p p r o x i m a t e l y 80% o f chart width between these two points.
W i t h i s o l a t i o n v a l v e a d j u s t e d t o 20 GPM, s t a r t S a n b o r n r e c o r d e r a t 100MM/Second p a p e r s p e e d .
Open i s o l a t i o n v a l v e f u l l y a s r a p i d l y a a p o s s i b l e .
AIRMOTOR PUMP EVALUATION
Replace electric motor pump with Gast Air Motor driven pump.
P u r g e s y s t e m p e r 1 . 1 . A d j u s t a i r p r e s s u r e t o p r o v i d e 24 t o 25 GPM r e c i r c u l a t i n g f l o w . Run a i r m o t o r f o r o n e h a l t h o u r ~o s t a b i l i z e . R e c o r d a i r p r e s s u r e s u p p l i e d t o m o t o r .
Zero per 1.2.
Calibrate per 2.0.
Date 12/01/87 REV. 1 /8 /88 74 108935 Page 3 o f 11
AEOC-TR~9-6
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
WIDE RANGE FUEL FLOWMETER
CALIBRATION DATA SHEET NO.
SERAPHIN FLASK CALIBRATION
DATE=
TIME-START: AMB. TEMP. STLRT:
STOP: TEST NO: RECORDED DATA
NOM FLOW TIME VOLUME RATE (GPM) (SEC} (GAL)
• 5 1 . 9 9 8 2 • 5 1 . 9 9 8 2
1 . 0 5 . 0 0 0 3 1 . 0 5 . 0 0 0 3 2 . 0 9 t 9 9 5 5 2 . 0 9 . 9 9 5 5 4 . 0 9 . 9 9 5 5 4 . 0 9 . 9 9 5 5
STOP:
PULS IS + / - I 1 ~ 2" 1" SYS
WATER TEMP (F)
S¥S. PRESS (PSZ)
CALCULATED
NOM. FLOW RATE (;~EF.)
. 5
. 5 1.0 1 . 0 2 . 0 ]11
4 . 0 4 . 0
TEST VOI£TME (~AL)
TEST FLOW ~-rACTOa RATE (;PX) (FU~ES/aAL)
DATA BY:
APPROVED:
Date 12 /02 /87 1 0 8 9 3 5 Page 4 o f 11
75
AEDC-TR-89-6
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
WIDE RANGEFUEL FLOWHETER
CALIBRATION DATA SHEET NO. 2
PROVER CALIBRATION
DATE:
TIME - START:
STOP:
TEST NO.:
PROVER VOLUME:
RECORDED DATA
~J.) TEST FLOW RATE(GPM),
NOM. FLOW RATE (G~)
8 15 3¢ 80
120
2" PULSES
AMB. TEMP. START:
STOP:
GALLONS
I "
PR e & E FACTOR-1010 COMPUTER PRINT OUT
WATER SYS. PRESS T~. (. r | (PRz)
CA~TED~2~ TIME(SEC.)
NOTES:
DATA BY:
APPROVED:
Date 1 2 / 0 1 / 8 7 I1 ) DELETED-T] HE (SEC)
REVl-e-8a 2) ADDED CALC. TZME
108935 Page S o f 11
76
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
AEDC-TR-89-6
WIDE RANGE FUEL FLOWMETER
CALIBRATION DATA SHEET NO. 3
MAINSTREAM MZTERCALIBRATION
DATE:
TIME - START:
STOP:
TEST NO,:
PROVER TEST VOLUME m
~|~TEST FLOW RATE(GPM), PB #
AMB. TEMP. - START:
- STOP:
GAL.
& "K" FACTOR-1010 COMPUTER PRINT OUT
gOM. FLOW RATE (REF}
20 40 60 80
120 . 1 4 0
160
200
NOTES:
~uLSES 2"
%DEV. -
WATER TEMP. K FACTOR "F (PULSES/GAL)
"K -X(=oo)l • (TEST) K
( 2 0 0 )
x ]~oo
CALC % DEV.
-O-
CALCULATED TIME (SEe.)
I I I I
BY:
APPROVED.
Date 1 2 / 0 1 / 8 7 R[V1-8-88 (1) DELET[D-TIME(SEC)
(2) ADD[D CAl.(;. TIME
108935 Page 8 o f 1 1
77
AEDC-TR-89-6
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
WIDE RANGE FUEL FLOWMETER
CALCULATION SHEET - t DEVIATION
DATE:
TEST NO. :
NOH. FLOW RATE (aZF)
,5 .S
1 .0 1 .0 2 . 0
TEST FLOW RATE ( G ~ )
K FACTOR (PULSE~GAL)
4 .0 4 .0
8 .0 1 5 . 0 30.0 60.0
z2o.o 1 8 0 . 0 - 0 -
% DEV.
% DEV. CkLCU/.&,TED AS FOLLOWS:
% DE~. (TEST) (180 GI:~ K
(zeo Gl=~)
X 100
BY:
APPROVED:
Date 12 /01 /87 1 0 8 9 3 5 Page ? o f 11
78
AEOC-TR-89-8
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
WIDE RANGE FUEL FLOWMETER
TEST EQUIPMENT LIST
MANUFACTURER
ANADEX
DIGITAL EQUIPMENT
SANBORN
SERAPHIN
WAUGM CONTROLS
DESCRIPTION
F-DC CONVERTER
PRINTER
STRIP CHART RECORDER
i0 GALLON VESSEL 5 GALLON VESSEL 2 GALLONVESSEL
MICROPROVER PROVING COMPUTER PROVER COUNTER MINICOUNTER PRE-AMPLIFIER
MODEL NO.
P1-608
DEC'WRITER I I
60-1300 B
M M M
700-08-15 1010 670-1 427 A-11
239
17118 14260 14836
10092
Date 12 /01 /87 108935 Page 8 o f 11
79
o
, - I m
N
G0
m
t ,o
o
IHROI"ItJNG W4L~
S B ~ FLASK
Z'CaL
I" COL
'iHROTaNO VAL~
PULSES
1" E
III
~ I" ClXl.
2" LE11~t
Igl
I~OII~tA.AlION FLOW
FLOW . , m B m
l o TANK I
llfirJIml TJ~I. BI~ l~P 81~&PiJllg lq,&.ql£ c ~
C;:J t l ) m - . I
z
m m r ~
'-iPI
0
f " t m
m
cp
' - - I r ' r l
CO ,.,,r.J
Q
I"r l
Q
0
1toOl"lUNg VAL~
2"COIL
1"
HmLAI~I
/ t I ~ww cut'A'tt°N
J~ 1* COIL
]---f-] I I s , ~ , o m ,
i[ ~ ~o~.
NO
PULSES ~_~ 1" MElI~ PUL.~S
FLOW
SYS~ PULSES X FACTOR ( P / a ~
I 8 ' ~ ~ m UP l int~VlOt CM, , , I~ ,
t ~ r r l
r'T'I
- r l
I ' r l
- r l I " " , 0
X r r l - - i r r l
- - I m
---I
IT'D
- I ,m
do ? {D
O0 t ~
"-4 r r l
F., C3 l..a
O0 ".,,d
WIDE RANGE FUEL FLOWMETER
SYSTEM CALIBRATION
DATE:
TEST NO:
l,.a Q O0 U~
(,,,'I
irrl
0
+2.0
+I.0
0 6 - e - q Z
~ L I d I,,~ O .
-1.0
- 2 . 0 0 .5
] -
1.O
FLOW RATE (GALLONS PER MINUTE)
TEST PROCEDURE WIDE RANGE FUEL FLOWMETER
I
- I :
_|: -1-
-I- I-
I
AEDC-TR-89-6
APPENDIX B
TEST DATA AND CALCULATIONS
WIDE RANGE FUEL FLOW'METER
83
WZDERANGE I r O E L ~
CJkLZBRATZON DATA 8ur~ETHO. 3
NAZNSTRLtNIqZTERC),LZBRATZOH
naTz. / - / , 4 - - B $
STOP: ,4' : ~7..
I:~O'v~R TEST VOLUXE "
(I~ TUT 7LOW P,~Tz (ozm), s ~ . . 7 z 4 GA•b/O
Pc, & mKW F&CTOR-1010 C~gGsD2T~ PRINT OUT
t DEV. -
HOTES s
Jums. ~ a ~ . - sTAnT: 78 "F
- STOPs 7 $ " F "
AEDC-TR-89-6
rK " -K "J ,
(:oo)
JUPPROVED-"
Date 22/01/87 REV1-8-88 I l l ADDEDDELETED'TIHE(SEC)cALC. TIRE
FIGURE B.1.
lo8935 Page 4 o f 11
MAINSTREAM METER CALIBRATION. (I of 4)
84
AEOC-TR-89-6
~ ~ $ $ ~ ~ 8 ~ TURBINE METER TESTREPORT ~ ~ $ ~ ~ :
14 JAN 88 1 5 : 4 0 M~TER I D : WRFF DATA BY:
" T ~ ' r " ~o. 8 ~ . ~ P ~ I o ~ 3 ******************************* CALIBRATION DATA * * * * * * * * * * * * * * * * * * * * * * * * * *
RUN RUN METER DATA 2 1 COUNTS 11724 .91 11727 .81 METER FACTOR - - 4 7 4 . 6 0 2 2 9 4 7 4 . 7 1 9 7 2 NEW METER FACTOR: 474.66113
PROVER DATA FLOW RATE 1 9 8 . 8 8 1 9 8 . 8 4
e~,~ "DCV ~.,.,-O -
RUN RUN METER DATA 2 1 COUNTS 1172B .12 1 1 7 2 7 . 5 0 METER FACTOR - - 4 7 4 . 7 3 2 1 7 4 7 4 . 7 0 7 2 7 NEW METER FACTDR: 4 7 4 . 7 1 9 7 2
PROVER DATA FLOW RATE 1 8 0 . 6 0 1B0.74
-I- .O ! '7*
RUN RUN METER DATA 2 1 COUNTS 11732.20 11730-;66 METER FACTOR - - 4 7 4 . 8 9 7 4 6 4 7 4 . 8 3 4 9 6 NEW METER FACTOR: 474 .B6621
PROVER DATA FLOW RATE 1 5 8 . 2 8 15B.76
RUN ~ RUN METER DATA 2 1 COUNTS 11730°97 1 1 7 2 8 . 5 2 7 , METER FACTOR - - 4 7 4 . 8 4 7 6 5 4 7 4 . 7 4 8 5 3 # . 0 NEW METER FACTOR: 4 7 4 . 7 9 8 0 9
PROVER DATA FLOW RATE 1 5 7 . 8 1 1 5 8 . 2 4
RUN RUN METER DATA 2 1 COUNTS 11734oB9 11734 .41 e'9 METER FACTOR - - 4 7 5 , 0 0 6 3 4 4 7 4 . 9 8 6 8 1 ~ o 0 / o HEW METER FACTOR: 4 7 4 . 9 9 6 5 8
PROVER DATA FLOW RATE 1 3 8 . 7 0 13B.93 • ~ : 1 ( ~ $ ~ ~ S $ ~ TURBINE METER TEST REPORT S ~ l ~ X ( ~ : l ( ~ : k ~ )
FIGURE B.1 HAINSTREAH HETER CALIBRATION. (2 o f 4)
85
AEDC-TR-89-6
I ~ = = ~ $ ~ $ ~ = $ ~ t ~ = = = = CALI~RATZON DATA ~ ~ ~ ~ ~
RUN METER DATA 2 COUNTS 1 1 7 3 8 . 6 4 METER FACTOR - - 4 7 5 , ~ 5 8 2 0 NEW METER FACTOR: 4 7 5 . 1 7 6 7 5
RUN 1
1 1 7 3 7 . 5 6 4 7 5 , 1 7 5 3 1 -t- . t t ~),
PROVER DATA FLOW RATE 117o78 l i 8 , 8 7
RUN RUN METER DATA 2 1 COUNTS 1 1 7 5 0 . 6 7 1 1 7 4 5 . 8 2 METER FACTOR - - 4 7 5 . 6 4 5 0 1 4 7 5 , 4 4 8 7 7 NEW METER FACTOR: 4 7 5 . 5 4 7 1 1
PROVER DATA FLOM RATE 1 0 0 . 6 7 1 0 0 . 7 9
,.:s?.
METER DATA COUNTS METER FACTOR - - NEW METER FACTOR: 4 7 5 . 5 4 7 1 1
PROVER DATA FLOW RATE
RUN METER DATA 2 COUNTS 1 1 7 5 6 . 4 0 METER FACTOR - - 4 7 5 , 8 7 6 9 5 NEW METER FACTOR: 4 7 5 , 8 7 0 B 4
RUN 1
1 1 7 5 6 , 1 0 4 7 5 . 8 6 4 7 4 +
PR0VER DATA FLOW RATE 7 7 . 8 1 7 8 , 4 0
RUN RUN METER DATA 2 1 ,r/ COUNTS 1 1 7 6 1 . 3 8 1 1 7 6 3 , 9 0 ~| #e METER FACTOR - - 4 7 6 ° 0 7 8 6 1 4 7 6 . 1 8 0 6 6 '~" " NEW METER FACTOR: 4 7 6 . 1 2 7 6 3
PROVER DATA FLOM RATE 6 0 , 3 7 6 0 , 3 8 ~ $ ~ S ~ t ~ = ~ t 1 $ ~ $ S ~ t ~ = ~ TURBZNE METER TEST REPORT S I = = t ~ I ~ = ~ ~ I I S = =
14 JAN 88 16¢23 HETER ZD," MRFF DATA BYI
* * * * * * * * * * * * * * * * * * * * * * * * * CALIBRATION DATA * * * * * * * * * * * * * * * * * * * * * * * * * * *
FIGURE B.1 MAINSTREAM METER CALIBRATION. (3 o f 4) 86
86
AEDC-TR-88-6
RUN RUN HETER DATA 2 1 COUNTS 1 1 7 6 6 . 5 9 1 1 7 6 4 . 0 5 HETER FACTOR - - 4 7 6 , 2 8 9 5 5 476,18676 NEW HETER FACTOR; 4 7 6 . 2 3 8 2 B
PROVER DATA FLOW RATE 3 5 . 9 7 3 7 , 3 5
-p •
RUN HETER DAYA 1 COUNTS 1 1 7 5 8 . 4 9 HETER FACTOR - - 4 7 5 . 9 6 1 4 2 NEW HETER FACTOR: 4 7 5 . 9 6 1 4 2
PROVER DATA FLOW RATE 1 9 . 9 4
Z $ ~ ~ $ ~ * ~ ~ TURBINE HETER TEST R E P O R T ~ ~ $ ~ ~ I
14 JAN BB 16 :31 HETER ZD: WRFF DATA BY: " I"E'ST k / o . 8 g - ~) P/ i~; E 3 o F 3 • ~ $ $ ~ $ $ ~ $ Z ~ ~ CALIBRATION DATA ~ c $ ~ c ~ $ ~ , ~ Z ~ $ ~
HETER DATA COUNTS HETER FACTOR - - NEW HETER FACTOR¢ 4 7 6 . 2 3 8 2 8
PROVER DATA FLOW RATE
RUN RUN HETER DATA 2 1 COUNTS 1 1 7 5 7 . 8 B 11754 ,91 HETER FACTOR - - 4 7 5 . 9 3 7 0 1 4 7 5 , 8 1 6 4 0 NEW HETER FACTORZ 4 7 5 , 8 7 6 7 0
PROVER DATA FLOW RATE 2 1 . 9 6 2 1 . 9 8
'4" .7. t, '~o
FIGURE B.1 MAINSTREAH METER CALIBRATION. (4 o f 4)
8?
AEDC-TR-89-6
HZDB RAHAB lq[TB y. L F ~
CkZ,CUI,ATZOH 8HXET - t DEVZ&TZOH
~2s= 1 -18 -8~5
5"zsT ~ o . = 8 8 - L o ~" 8 8
NOM, ~ TEST FZJ0W RATE ( n z r ) ~ T z ( a ~ )
, 1 . 0
2 . 0 2.1. 2 . 0 2. , ! I O
1 2 . o ?... o :p 4- 4 . 0 ,,~.~ I O 4.0 ~I-.IO 3
8 . 0 ~ . 4 ~ 1 5 . 0 ~ o . ,¢-o 3 0 . 0 . 5 o 8 0 . 0 G ¢ ~ . "7 I
L20.O I 2 3 • ~f. . 1 8 0 . 0
t D E V .
t D E V .
J 7 9 . 41,3
~ Z , ATED U FO~J.OW8-"
(28o aim)
K T&CTOR (P' , 'LSES/~L)
4.") o , 17,.
~!- 7 0 . s o r ~ r ~ r t w J J l ~ ] 3 ] ~ 5 1 r F t ~ -Z:]l
. ' ~ J E S T 4 1 1 ' , S I r r - ~ l ~ l r l : l l ~ l l
X 200
DIW'.
- I . & S " - - I . ,5"7 - . 9 7 - . S q - - - I S O - . R 3
- , + 9
- , 3 9 - . O L .f- . 0 1 • 1'- . I?..
" 0 "
hate 12/Ol/87 1 0 8 9 3 5 Page
FIGURE B.2. SYSTEM CALIBRATION. (1 of 5)
7 o f 11
88
AEDC-TR-89-6
WIDE RANGE FUEL FLOWMETER
CALIBRATION DATA SHEET NO. 1
8ERAPHIN FLASK CALIBRATION
DATE. l-lS-SS
TIME-START-" ~ .' I "P
STOP: I o : 3 S " TEST NO: R R - i o RECORDED DATA
CALCOLNI~D
AMB. TEMP. START-"
STOP" 51; o F
• +/ -z~ + - . $ o
• ~-. ( , , .
- - . 9 0
J SYS. ] WATER PRESS
8Y8 TEMP (F) (PSI)
~.- :,.~ ,,, I ~ I ~ I • ~ z ~ I ~ I 3"8 I ~ 7 0 ~ ~ ~ 1
. . I ~ ~ I ~ ' ~ I ~'?_ : ~ ~ I ~ - ~ 1
NOM. FLOW TE8T VOLUME ~T'- ( ~ F , ) . (GAL)
.5 2.. o o o 4.-
.S ~ _ . o o l o °
1 . 0 o o 2 . 0 ~). 9 ~ 2 .~" . . o 4 . 0 . I & 4 . 0 ~ , 7 8 ~ J 4 -
TEST FLOW
• 4-8~-
• 9 ' q - 3
2 . , I o,5" " 2 . . 1 1 o 4.q I o & 4 - . I o 3
. ¢ 9 ~ & 3
2 . o ~ 4
DATA BY: ~ , , ~ / p ~ - ' -
APPROVED: ~ • TH,~-D I ~ . 0 ~ C o ~JDur -TED /%.'/" 2 ,o GPP?
, ~SG. l z ~'¢c. -r.Z6-,~.:
9. ~ 94~ e
~ " FLoI,J ~-I"P.~I~H'I ' lCI~IE'R. P-E IAOV~ ' I~
S Y ~ T ~ H ~ . E P ~ o E ' D E E l : o R E P- .uN
D a t e 1 2 / 0 2 / 8 7
K-FACTOR (~LSES/GAL).
4-/, r,. 91 4 & ' 7 . 2 . 7 4"to .1:- 4- '?o . " / z 4 7 z .!
,~-" J , .b"o "1-" /z. ,
15"$ I~'o 4-?Z./ 'FTZ..~'0 I~ F A c v o l l
P I l l o1~. '1"o T ~ I $ R u M
108935 Page 4 o f 11
FIGURE B.2. SYSTEM CALIBRATION. (2 of 5)
89
AEDC-TR-89-6
WIDE P.II|GE lV~EL P L O W ~ T D
CALZBRATION DATA S l e E T NO, 2
PROVER ~ B R A T Z O N
~,,=z: l - i S -a8
stop- / / ; 14 O
TEST ~o. : 8 8 - t !
P R o v ~ ~ , : 1 4 . 7 , ? . 4
AHB. TEXP. 6TARTt
STOP:
G,'~,LONS
E7°F 6 o ' F
RECORDED DAT&
(.L~ ~ s T FLOW R~TE(GI:5(),
HOH. FLOW
6O
q I~
PsJe & K F&CTOR-1010 COMPUTER PRZHT OUT
~ T & BY:
~,PPROVED:
Dat:e 12/01/87
FIGURE B.2. SYSTEH CALIBRATION. 90
108935 Psge 5 o£ 11
{3 of 5)
90
AEDC-TR-89-6
~8 JAN 88 l l : O S H~TER I D | l ~ p ~,'-,TA I~Y:
T g S T /do. 8 G - I I P ~ E ' t l . o F 2
RUN I~TER DATA 3 COUNTI; 116?6-~S N~ 'ER FACTOR --- 4 7 2 . 6 ~ f 6 8 HEM NETEK FACTOR: ~ T 2 . 5 4 2 7 ~
PROVER DATA FI.OM RAIE 8 ,49
RVN RUN 2 I
1 i 6 7 1 . 4 ! ]1678 .70 4 7 ~ . 4 ~ Y 2 ~72.73193
8.3'z I h S l
RUN HETER DATA 2 COUNTS I 161tO, I 0 METER FACTOR '" - 47;[, 82080 NEW HETER, FACTOR.: 472 .85 ,$75
RUN I
1 |682.8]L 472,88647
PROVER ,PATA, FLOW l~Ik'1~ 16.40 16. I B
RUN RUN HETER DATA 2 I COUMTS . . . . . . . . . I t722 ,S I ! 17Z7.44 HEr El~ FI4CTOR. .... 474 .,50S37 4,74.70507 HEW MF.TER. FACTOR: 4~4 , .&O3 ; IZ
PROVER DATA FI..Okf RATE 3D , 6"0 30,4:7
RUN RUN METER DATA ~. I COI)N'rs . . . . . . . . ] 1 7 2 ~ , El | 1727. | 0 N&'TER IrACTOI~ ..... 4.74, 80078 494,6g091 NEld NETf.R F.ACTOR, 4.74,74SII4.
PROVER D~t T'P, PI.OI,I KATE 60 . 71 60.6g
IWN HE'I'ER PATA 2 COMdl"S . . . . . . . . . . 11741.41 IIIETER FACTOR. - - 47: l . ZTOZ6 NEleJ HETER. FACTOR.," 475.,.qO~Oll
RUN 1
I | 7 4 3 . 3 2 ,I.75. Jr476S
PROVER. DATA FLOW RATE 123. O6 I t 2 ,94 .
. . . . . . . . . . . . . . . . . . . . . . . . .
FIGURE B.2. SYSTEH CALIBRATION. (4.of 5)
91
A E D C - T R - 8 9 - 6
J8 JAN 88 11:3+ HETER J D: i/RFF " ' . ; , ' . E, ~ . . . . . . . . . . . . . . . . . . . . . . . . . . .
. , b ,
RUN RWI HETER. DATA 2 I COUNTS -. l 172S. 88 ! 1726.S$ I~-rF.R F~'roR 47+.76t~3 4-74,6(,ilP~ HEM H£TEP, FACTOr: 474.71406
PROVF.R, D/J~T'A FI.O~ RATE ! TF ,41 l ? t ,.~2
"Z'~'T'¢)o, ~tS-II P A G ~ 2 o F 2
FIGURE B.2. SYSTEH CALIBRATION. (5 of 5)
92
AEDC-TR-89-8
WIDE RANGE FUEL FEOWMETER
CALt~TLATION SHEET - % DEVIATION
D,~TZ: / - 1 ~ ) - 8,S
TEST N O . : 8&-IZ~ 88-13 Lo6,J PEE'~SuR.~ CALII~R.~)TION
NO](. FLOW RATE (HEF)
. 5
. 5 1 . 0 1 , 0 2 . 0 2.0
! 4 . 0 4 . 0
8 . 0 1 5 . 0 3 0 . 0 6 0 . 0
1 2 0 . 0 1 8 0 . 0
% DEV.
% DEV.
TEST FLOW
. 4 . 3 0
. ~ "~ "1- , 9 9 - 2 . 9 9 R
'2 . o 3 R
.~/. 9 z ~ g , '91 &
g . ' ] 6 I-~ .4g
1 2.. 4-. 12.. 1 7 &,/.,3
CALCULKTED AS FOLLOWS:
K (ZSO a l ~ )
K FACTOR (]L:'ULSES/GAL)
4 7 o . ? 1 4 . 7 4 . &7 ~ -75 . I z 4 7 ~ & . S 7 47.1 ,4"7 4 7 : r . 5 " 7
473 .~
473. 8 2 4 7 3 . oz 47'I-. P t .4.74-. 7 z • ~. 7.,S", z o
? 4- . &~.
, 4 7 4 . 7 2 .
X 1 0 0
%DEV.
- - r 8 0 - . - . 0 1 t" , 0 8 t" . 3 . . 9 - , 7 - & -- , ; Z ' k
- . 2 . 4 - - , 2 ? .
-I., . 0 7-
,f,," , I 0 - - . 0 7 . ,
• u,'J~O,,'zo, "~..,.~:¢.,:t~
Oate 12/0118" I 1 0 8 9 3 5 PagQ
FIGURE B.3. LOW PRESSURE CALIBRATION. (1 of 5)
T o£ 11
93
AEDC-TR-89-6
MIDERANGE FUEL FLOWMETBR
CALIBRATION DATA SHEET NO, 1
SERAPHIN FLASK CALIBRATION
D A ~ : /-tp - S s
TIME-START-" ~: ,~.o
, . , RECORDED DATA
AHB. TEHPo START:
8TOP:
CALCULATED
6 o eF
5~°F
~" "RIO-JIll ¢,; r l : IE
i ~ ~[, £-':w,-]l EeB
DATA BY"
APPROVED,
L o b J P P . ~ s u ~ E CAL t~ ,P . .ATeoU
Date 1 2 / 0 2 / 8 7 108935 Page
FIGURE B.3. LOW PRESSURE CALIBRATION. (2 of 5)
4 o f 11
94
AEDC-TR-89-6
WIDE RANGE FUEL FLOWMETER
CALIBRATZON DATA 8][ l~T NO.
PROVER CALIBRATZ~
2 2 x ] ~ - ~JU~Ts I ~:,4..~" N,m. 2']me. STJU~s
' 57 s=oP, BTOPI /
~ S T ~0 . S ~ 8 - 1 3
P R o , ~ v o L ~ s "2 4 . 7 2 4. r .A~,On
RECORDED DATA
(J.~ TEST FLOH ]~kTl (GIN),
5 6 " F
Ps, & X FACTOR-1010 C0NPUT]Dt I ~ Z ~ OUT
RON. FLOW I ~.TLBB8 I~TER 8Y8. l~UB88CALCUZ, ATP~ ex~ (G~) I 2. I z- ~w~. ( .7 (Psz) TZn(SZC.) (~
• 5 ~ 6 6 S I I ~ 7 7 3 ~ G 8 =is 9 . 1 3 . 1 3 8
120 I ~ ! i ~ 6 ~ ? ] I , '5 .,~.'3 .I 1 , 9 # Z . 180 t ] v31 5 e~'i I r,5 1"7 8 . 3 9 9
N0'1~8 •
I-o IA/ U ~ r r
Pe..k-'s:~ u p-a ~ L - ~ se.A'r lON NoT" 2 E ~EP- .o~ ~
DATA BY:
,1LIPPRO'~D: ~
Date 1 2 / 0 1 / 8 7 108935 Page REVI-8-88 I l l ADDEDDELETED'TIHE(SEC)cALC. TIHE
FIGURE B.3. LOW PRESSURE CALIBRATION. (3 of 5)
S o f 11
95
AEDC-TR-89-8
19 JAil 88 12:$3 H£1"~R ID: W~'F "I'E~T NO. IIII-I~, i..,o+,,J /:)¢~J;~uP.,.(: C ~ l i l , .
RUN RUN METER DATA • I COUNTS 11686.30 1 1 6 8 5 . ~ HET£R F,~'I"OR ~73.03930 ~72.g96S~ N£'WHET~R ~-ACTOR: 473.01806
PROVER DATA FL0~RAT£ 13.46 13.59
P R G { £ ol~
RUN RUN I~.T£R DATA 2 I COUNTS - 11707.01 11704.40 HETER FACTOR 473.877£B 473,771P7 NEW HETER FACTOR: 473,8249S
PKOVEL DATA FLOW RATE 6.96 7.¢k¢
t4EI"ER DATA COUNTS HETER FACTOR NEMHKTER FACTOR:
PROVER DATA FLOr iSTS
4"?3 • S2495
RUH HETER DATA 2 COUNTS . . . . . . 11731.0$ P~TER FACTOR - . 474.850S3 NEM HETER FACTOR; 474 .8 i 07 t
PROVER DATA FLOMRATE 31.21
RUN !
11729.07 474, 77050
31.Og
RUN I~E'rER DATA 2 COUNTS 11726.19 HETER FACTOR .... 4./4.68a6] NEW HETER FAGTOR: ~7#,71630
RUN !
I I 7Zll .S$ 4 7 4 . . 7 4 9 7 f
I ~ 0 K R DATA FLOW RATE SS • 30 6'8.42. ~ ¢ ~ : ~ . ~ . ~ : ~ ' ~ : t / : ~ : ~ : ~ ¢ , ~ TURBTNE HETI-R 'TEST RE-PORT ~ . ~ . ~ ' ~ : ~ , , P ~
FIGURE B.3. LOW PRESSURE CALIBRATION. (4 of 5)
96
AEDC-TR-89-6
19 JAN B8 13:24 METER ID: WRFF DATA BY:
• ~ ~ ~ ~ ~ $ ~ CALIBRATION DATA ~ ~ ~ ~
RUN RUN METER DATA 2 1 COUNTS 11.739.62 11739°60 METER FACTOR - - 475.19799 475,19726 NEW METER FACTOR: 475,19775
PRDVER DATA FLOW RATE 124,12 123o90
RUN RUN METER DATA 2 1 COUNTS 11725 .28 11725.30 HETER FACTOR - - 474 .61743 474.61791 NEW METER FACTOR: 474 .61767
PROVER DATA FLOW RATE 176,63 176,15
FIGURE B.3. LOW PRESSURE CALIBRATION. (5 of 5)
97
AEDC-TR-89-6
WIDE RJUqGE FUEL FLOWNETER
~%.T.CUL~TZON SHEET - % DIFTZ~TZON
DATE: 1 -2 1 - I 8
TEST XO.: 88-17 88-18
HOM. JT,OW TEST FLOW X~,Tm (nZF) R~TE (O]m)
.s ..5"3~
. s . s ' j 4 ] . .0 I . 0 4 . 7 1 . 0 I , 0 q-J~ 2 . 0 2 . o e) ~ 2 . 0 ':P., • '9 f
. i 4 . 0 d- , o 4..(" 4 . 0 4 , o & ' 1
8 . 0 . ~ 8
3 0 . 0 2 8 . ' ; )8 8 0 . 0 4 : o . I I
1 2 0 . 0 I I =J. 8 2 . 1 8 0 . 0 I '? 9 , K O
% DEV. ~ T E D U FOLLOWS:
][ FACTOR (~'~" ~SE~GAL ) % DZV.
4¢0. 417 - 3 . o t 4)'4; | . 4 1 6 -- ,Z ,BO
?,.7 -- | . 9 9
4 " ~ " L ~[~ - ~ - i , o 7 4 / - .
4 7 / . SoS- -- , ~ ,8 4 ? 1 . r ~ - 3 .-. , ( , 3
~7z. 6"3 - , 4-G a Tz. i;~ - • ~@ 4-'#~. ~.$ - , o
~ " / 4 i - . 6~ i - -- ,07,,
4 7 4-. 7 z - 0 -
X 1 0 0
K (].80 a~ ) ",
A]PI:~OVED z ~ _ _
Date 12/01/87 108935 Page FIGURE B.4, STABILITY CALIBRATION. NO. I (1 of 5)
? o£ 1 2
98
A E D ~ T ~ 8 ~ 6
WIDE RANGE FUEL
CALIBRATION DATA 8IIEBT NO. 1
BEIEk,PHZN FLASK CALIBRATION
~ : s , 1 - 3 4 - f l
TEST NO: RECORDED DATA
~ ' J L ~ D
HON. FLOW TEBT VOLUNE ~ ( ~ ' . ) ( ~ )
• 5 . 2 . 0 0 0 3 ~ ; . 5 / r f ~ ; o 3
.. 1 . 0 Sr o o l ~17
3 . 0 I 0 . o o o ~ I 2 . 0 9. q ? 0 7 3 4 . 0 9 . 9 S l J,~. 4 . 0 'L, 9 3 5 0
DATA BY:
~UPPROV~D:
AXB. 'L']DG ~, 8 T ~ s
8TOP:
8Y8. WATER 1~E88 sys.:l !'TIWp~ (J') I z~sz)!
. . . . ! ~ 1 Z ~ - , , ~ - - - - - - J = . ~ - ~ i ~ I 5p, I
. ~ . : u. I ~,.~ I S I I ~ _ $ ~ 1 ~ 1 2 ~ ' ~ 1 y ~ q m . I &9 I .~B I ~ ~ I ~ I
'L~ST FLOW
. 5 3 9 , ~ 3 V
• q , o ~ ? I , ~ ' 1 8
~ . o q l
' I . 0 6 7
.uJJJ'r ~JO.._.rr ~ . E p _ o L - l ~ B ~ F o l a . E gLUl~ / . . A s ' r ~ - E ' R o 3 : 3o P M I - z o - 8 8
K-F&CTO2 (I~.TI,SES/G&L) _
f ' ~ " Y/7 ?&l .,/s(
I / ' / I . 3 57 9'~,l .~J.S ¥ ?1, so.5 Ll'l ~ . 7 5 3
Date 13/02/87 108935 Page
FIGURE B.4. STABILITY CALIBRATION. NO. I (2 of S)
4 o f 11
99
AEDC-TR-89-6
WIDE RANGE FUEL FLOWlO,TER
CALIBRATION DATA SHEET ]NO, 2
PROVER CALIBRATION
DA=. l -~,i,~f
,TO,, 3" 5y TEST XO. s ~ 8, - f8
RECORDED DATA TEST FLOW RATE(GPM),
ST,aT, 7 I°F stop, 7 O°P
GALLONS
Pliw Ii K FACTOR-1010 COMPUTER PRINT OO'1'
NOM. FLOW PULSES RATE (GPM) 2" 1"
4-S" I & 9 9 6 9S ' I 15 Z 8 ~, 4-S" 4 -~ ! I Z 30 2.1 62-<.- ~..~ g 8 3 60 I g S 3 I J :3 9 ~ S
120 J ~ !.~S 7 mo.~
W~TZa SYS. R~ZSS CaLCULaTED : ~ p . (or) (psz ) TZ)B(SZC.)
- / 3 ,~ 8 19 9 . & s~
7 0 .¢-~" .Yl . I S d ? o 'l 'f 7. ÷ , ( ,7 9 70 ~-~" I Z . . S S l v o 8 , Z 7 8
XOC~S: N o T R . E : t £ ' P - o E ' ~ I':1~101¢ T o P - U N "
APPROVED:
Date 1 2 / 0 1 / 8 7 108935 Page
FIGURE B.4. STABILITY CALIBRATION. NO. 1 (3 of 5)
5 o f 11
100
AEDC-TR-89-6
~ ~ ~ ~ ~ CALIBRATION DATA I ~ I $ ~ $ ~ * ~ X ' * * * * * ~ - .
RUN METER DATA 1 COUNTS 11675.45 METER FACTOR - - 472.60034 NEW METER FACTOR~ 4 7 2 . 6 0 0 3 4
PROVER DATA FLOW RATE 7 . 0 7
~ $ ~ $ ~ ~ ~ ¢ ~ TURBINE METER TEST REPORT ~ $ ~ ~ ~
21 JAN B8 14:47 METER ID: WRFF DATA BY:
~ i ~ ¢ ~ ~ ~ ~ CALIBRATION DATA ~ ~ ~ ~ ~
RUN METER DATA 1 COUNTS 1 1 6 5 5 . 3 6 METER FACTOR - - 4 7 1 . 7 8 7 1 0 NEW METER FACTOR: 471.78710
PROVER DATA FLOW RATE 8 . 2 3
$ $ ~ $ ~ ~ , ~ $ $ ~ TURBINE METER TEST REPORT ~ $ $ $ ~ ~ $ $ ~ * ~ $ ~
21 JAN 88 1 5 : 0 2 METER ID: WRFF DATA BY: TEST ~o. 0 ~ - IB P , ~ ¢ t eFZ
~ ~ $ ~ ~ $ ~ $ ~ $ CALIBRATION DATA ~ Z ~ ~ ~ ~
RUN METER DATA 3 COUNTS 1 1 6 7 1 . 1 0 METER FACTOR - - 4 7 2 . 4 2 4 0 7 NEW METER FACTOR: 4 7 2 . 5 2 9 0 5
RUN RUN 2 1
1 1 6 7 6 . 2 B 1 1 6 6 3 . 1 2 4 7 2 . 6 3 4 0 3 4 7 2 . 1 0 1 0 7
PROVER DATA FLOW RATE 7 . 4 3 7 . 5 9 7 . 8 4
RUN RUN METER DATA 2 1 COUNTS 1 1 6 7 6 . 9 2 1 1 6 7 5 . 1 0 METER FACTOR - - 4 7 2 . 6 5 9 9 1 4 7 2 . 5 8 5 9 3 NEW METER FACTOR; 4 7 2 . 6 2 3 0 4
PROVER DATA FLOW RATE 16.BB 1 6 . 6 8
FIGURE B. 4. STABILITY CALIBRATION. NO. 1 (4 of 5)
101
AEDC-TR 89-B
RUN RUN METER DATA 2 1 COUNTS 1 1 7 1 3 . 9 4 1 1 7 1 8 . 5 8 METERFACTOR - ~ 4 7 4 . 1 5 8 4 4 4 7 4 . 3 4 6 4 3 NEW METER FACTORt 4 7 4 . 2 5 2 4 4
PROVER DATA FLOW RATE 2 8 . 9 8 3 0 . 0 9
RUN RUN METER DATA 2 1 COUNTS 1 1 7 1 4 , 8 2 1 1 7 1 8 , 4 4 METER FACTOR - - 4 7 4 , 1 9 3 8 4 4 7 4 , 3 4 0 5 7 NEW METER FACTOR: 4 7 4 . 2 6 7 3 3
PROVER DATA FLOW RATE 6 0 , 1 1 6 0 , 1 5
RUN RUN METER DATA 2 1 COUNTS 1 1 7 3 1 , 6 3 1 1 7 3 1 , 7 2 METER FACTOR - - 4 7 4 , 8 7 4 5 1 4 7 4 , 8 7 8 1 7 NEW METER FACTOR: 4 7 4 , B 7 6 4 6
PROVER DATA FLOW RATE 1 1 9 , 8 2 1 1 9 , 9 5 ~ t * * t t $ $ t t ~ $ t $ ~ $ t , t $ ~ , ~ , TURBINE METER TEST REPORT ~ * t t = t S t ~ ~ = ~ J ~ Z ~
21 JAN 8S 1 5 : 3 7 HETER ZD: WRFF DATA BY: 1L~T Mo. g 8 - 1 8 p ~ E 2 oF2 . ******************************* CALIBRATION DATA ***************************
RUN RUN RUN METER DATA 3 2- 1 COUNTS 1 1 7 2 7 , ] 3 11726 ,91 1 1 7 2 0 , 3 5 METER FACTOR - - 4 7 4 , 6 9 2 1 3 4 7 4 , 6 8 3 3 4 4 7 4 , 4 1 7 9 6 NEW METER FACTORZ 4 7 4 . 6 8 7 7 4
PROVER DATA FLOW RATE 1 5 3 , 5 6 1 8 1 . 3 0 1 8 1 . 5 7
RUN RUN METER DATA 2 1 COUNTS 1 1 7 2 5 , 8 1 1 1 7 2 5 , 9 2 METER FACTOR - - 4 7 4 , 6 3 S 6 7 4 7 4 , 6 4 3 3 1 NEW METER FACTOR: 4 7 4 , 6 4 1 1 1
PROVER DATA FLOW RATE 1 7 9 . 2 0 179 .51
FIGURE B.5. STABILITY CALIBRATION NO 1 (5 o f 5)
102
A E D C - T R - 8 ~ 6
WIDE RANGE FUEL FLOWMETER
CALCULATION SHEET - t DEVIATION
DATE: I - 2.?. - 8~
T E S T ) ; O . : 8 a - 1 9 ~ 8 8 - ? - o
NOM. FLOW TEST FLOW
. s . , [ 1 3
. s . 3 1 , 4 . 1 . 0 , c~38 1 . o . 9 SB 2 . 0 2 . . C~¢- ~, 2 . 0 9 . 0 : 3 I
I | Z ,.O,.o . ' : °2°
8 . o 1 ~ . 8 5 1 s . 0 i ~". O 4 - 3 0 . 0 _ ~ 2 . f ,b" 6 0 . o ~, I . .6-8
L20.O 1 2 . 3 O 2 - L80.O 8 o~ ,q-2.
% DEV.
% DE%'.
CAI.,CUI.ATEDA8 FOLLOWS=
K (180 O ~ )
K FACTOR , (PU2,SeS~GAL)
4 7 0 . 9 6 4 7 0 . 1 6 4 7 7 - , S $ 4 " ) I , ? . 8
~ 7 2 . 6 7 . .4-7 I . 9 5
4 7 ! . S3 4 7 2 • I ~
~ - 7 ' ~ . 3 I 4 7 4 - . ~ ) 3 4 7 , q - . < - ' t 4,.7,9" • ' 7? .
X 100
i D r4 ,
- I . . S' l - :S. 4 (p -
- - , P 6 - ' . ,qG - . '~2.
-- . 6 1
-- , 1 1 -- . o . 9 + , 0 ~ - - , 0 6
BY:
APPROVED: e
Dato 1 2 / 0 1 / 8 7 10893S Page
FIGURE B.5. STABILITY CAi'IBRATION NO. 2 (1 of 5)
7 o£ 21
103
AEDC-TR-89-6
WID2 RANGE Ir~EL
8F.Rk~I:N ~ K G~ .TBRA~ON
TEST N0 :Ii'JL'OP: ~ A ~ "~'-~I:~'- RECO~U)~D DATA
I - Z t - S 8 sToP- ; 3 °r:
CALCULATED
NO](. FLOW TEST VOLUJ~
• s 2, ooo 8 • 5 / . q Y G ~
1 . 0 5-. o o 2-x" 1 . 0 .~r, o o ~.,.~ 2 . 0 ~ , ~ ) ~ ~ o
4 . 0 ~"7 4 . 0 ? , ~ t ,q. ~ s
D~T& B'l'- _ _ _ _ ~ _ ~
&PPROV2D 8
/~e-r'F. : "/3iS'l" t~;AS
TEST / 1 0 g K-FACTOR
, S ' I 3 4 ~ - . S l , ~1 + 4-~ir . 3 0 , q -
• "93~; , - ? o 2 , 0"1"2. <.~ Z • c ~
4 , 14-~. . 5~. 4 , 0 & o 7 I ?-~
ST^RTU-"D 3:,%" PH e~ I - Z / - J 8
Date 12/02/87 NoT
"/'E~'/" qJT'AfOl> PRoELE'I~s Foi~e.LrD r-ESsAT'IoDJ oF" " r ~ T A p i : ~ o x j ~_oo PH 1"E51" 1~..~5uM['l) I I ; O o A M I - ? - z - g 8 C o M P L t ; - ' r ~ o I1" '1"7 A M I - Z Z . - & 8 R . ~ £ R . o L r D Pl~toR. "ro ~.U~J-L.ig:;T'~ ~p-o I - Z 0 - 8
108935 Page 4 o f 11
FIGURE B.5. STABILITY CALIBRATION NO. 2 (2 of 5)
104
AEDC-TR-89-8
WIDE RANGE FUEL FLOWHBTER
CELZBRATZOH DATA BH]~JP ]lO. 2
PROVER CALIBRATION
D A T E : I - Z ~ - SS
TIME - 8TARTt I~ ~'3
STOP| 2- : °5
TEST 1~0. : B~)-Zo
vou z, :;2. q. 7, .ff
AMB. TEMP. START| (:LS""F
GALLONS
RECORDED DATA
(,L~) TEST 1~T2 (GPl() , FLOW
]~TH]~ 1fLOW PULSES ( G P X ) :1" 1 "
e 97 15 30 7 0 7 551 0 9 30 ~.O&61 a.s 8 ? Y 6 0 16 y~.s , -q s ~ ~ .
120 I 't J ~7 ~q ;L~ 180 13 V:L& 'eq3 3
HOTZS: NoT £E~: fe.o
Ps, & K FACTOR-ZOZ0 COMlqJ'J~,R PRINT OUT
WATER '8¥8. PRESS CALCULATED TEMP. ( ' r ) (PSZ) TZXZ (SEe.)
7 0 5 8 1~7. ~Z 6 7 o S& ~-q. 6.33 70 I;5 4.6. I 41 70 54- 2,4 . o ~ o ? 0 s 3 I Z . o _r,o)
pR. IoR . "To R.uM
DATA B ¥ : ~
A P I : R O V E D : ~
Date 1a/01/87 REV1-8-88 I l l ADDEDDELETED'TDIE(SEC)cALC. TIME
FIGURE B.5.
108935 Page
STABILITY CALIBRATION NO. Z (3 of 5)
S of 11
105
AEDC-TR-89-6
RUN METER DATA 2 COUNTS 11654.79 METER FACTOR - - 471.76391 NEW ~ETER FACTOR: 4 7 1 . 8 2 9 3 4
RUN 1
11658.02 4 7 1 . $ 9 4 7 7
PROVER DATA FLOW RATE 8 . 8 5 S .B2
RUN RUN METER DATA 2 1 COUNTS 1 1 6 8 0 . 8 6 1 1 6 7 4 . 1 9 METER FACTOR - - 4 7 2 . 8 1 9 3 3 4 7 2 . 5 4 9 3 1 MEW METER FACTOR; 4 7 2 . 8 1 9 3 3
PROVER DATA FLOW RATE 17.71 17.46 • ~ ~ Z ~ * ~ * * ~ * * ~ TURBINE METER TEST REPORT ~ , ~ ~ , ~ , ~
22 JAN 88 1 3 : 1 0 METER I [ l : WRFF DATA BY%
~o. 88 -2o P/tG~ £ oF'2. • ~ * ~ * ~ * * * ~ * ~ * ~ * ~ CALIBRATION DATA ~ * ~ * ~ , $ , ~ ~ , ~
RUN METER DATA 1 COUNTS 1165B .44 METER FACTOR - - 4 7 1 . 9 1 1 8 6 NEW METER FACTOR: 4 7 1 . 9 1 1 8 6
PROVER DATA FLOW RATE 1 3 . 3 3
RUN METER DATA 1 COUNTS 1 1 6 6 6 . 3 7 METER FACTOR - - 4 7 2 . 2 3 2 9 1 NEW METER FACTORt 4 7 2 , 2 3 2 9 1
PROVER DATA FLOW RATE 15.17
RUN RUN RUN RUN METER DATA 5 4 3 2 COUNTS 1 1 6 6 6 . 8 4 1 1 6 6 1 . 4 5 11671°96 1 1 6 6 4 , 3 2 METER FACTOR - - 4 7 2 , 2 5 1 9 5 4 7 2 . 0 3 3 4 4 4 7 2 . 4 5 8 9 8 4 7 2 . 1 4 9 6 5 NEW METER FACTOR; 4 7 2 . 1 4 2 8 2
PROVER DATA ELOW RATE 15.04 15.06 15.0B 15o10
RUN 1
11676.89 472.65B69
15.12
FIGURE B.5. STABILITY CALIBRATION NO.2 ( 4 o f 5)
]06
AF.DC~R49-8
RUN RUN HETER DATA 2 1 COUNTS 1 1 7 1 5 , 4 2 1 1 7 1 5 . 4 0 METER FACTOR - - 4 7 4 , 2 1 B 2 6 4 7 4 , 2 1 7 2 8 NEW METER FACTORS 4 7 4 , 2 1 7 7 7
PROVER DATA FLOW R#.TE 3 2 , 1 5 3 1 . 8 7
RUN RUN METER DATA 2 1 COUNTS ' 1 1 7 1 6 , 6 2 1 1 7 1 8 , 5 7 METER FACTOR - - 4 7 4 , 2 6 6 8 4 4 7 4 . 3 4 5 9 4 NEW METER FACTORZ 4 7 4 , 3 0 6 3 9
PROVER DATA FLOW RATE 6 1 . 5 8 6 1 , 3 6 Z ~ Z ~ Z Z Z Z ~ Z ~ Z Z Z Z Z Z Z ~ TURBINE METER TEST REPORT Z~ZZZZZZZZZZZZ~ZZSZSZ:
22 JAN 8B 13~46 METER IDZ MRFF DATA BY: , , ' ~ * * ' F ' ~ o . 8 8 - z o P A G r 2 O F
RUN RUN METER DATA 2 1 COUNTS 1 1 7 3 3 . 9 8 1 1 7 3 2 , 2 3 METER FACTOR - - 4 7 4 , 9 6 9 7 2 4 7 4 , B 9 8 6 8 NEM METER FACTOR~ 4 7 4 , 9 3 4 3 2
PROVER DATA FLOM RATE 1 2 3 . 0 2 1 2 2 . 7 0
RUN RUN METER DATA 2 1 COUNTS 1 1 7 2 1 . 1 0 1 1 7 2 0 . 4 6 METER FACTOR - - 474o44B24 4 7 4 ° 4 2 2 3 6 HEM HETER FACTOR: 4 7 4 . 4 3 5 3 0
PROVER DATA FLOM RATE 1 8 0 , 4 2 1 8 0 . 3 5
FIGURE B. 5. STABILITY CALIBRATION NO. 2 (5 o f 5)
107
A E D ~ T ~ 8 ~ 6
WZD le RAHGE FUEL lrLOWI42TER
CALCOL~TZON SHEET - i DEVZATZON
DATZ- I - Z -~ ' - 8 8
TEST No. s ~ 8 - 7.2. # 8 8 - 2 5 ~ I P - M o ' r D R . P U H P T ' W S T
HOt(. FLOW TEST FLOW n.~TZ ( n r ) RATE (OPX)
.~ . 5 " 5 1 . • 5 . , 5 " 3 2
1.o I . o 8 f 1 . o I . O B 8 2 . o / . q 3 f 2 . o I . q~-5~
_i 4 . 0 4 . o =;o 4 .0
8 . 0 9 . 2.1 1 5 . 0 I ~ . G 9 3 0 . 0 ~ 3 , 4 . 1 6 0 . 0 / 3 , - ~ 7
1 2 0 . 0 I 7 - 3 . 3 3 1 8 0 . 0 l S Z . ~ 5
'
t DZV. CALCULATED A8 FOLZ,OW8:
K F&CTOR (eu-,.azs/r, AL) t n ~ , .
• 1-73. ( , 7 - - . 2.2. 4 - 7 o . ~ z - - . B 6 4. ( ,6 .5" ,9 - I • "71 , 9 7 o . t [ o - - . ~ ? ,q. 6 P , 8 1 - - t . o 3 ~.- /~. . . GT, . , • A~.r,
r. ~rlJl, r..+.~ _ _ _ . j , ;
• 4 7 , ~ . + 1 -- , 4 - 9 ~ =.-+77' - , , q . l 4'~,9.-,61 __ • ...,L , 4 . ' / . = . 1 4 - - - . ~ 3 ,4 7 ~ ; , 7 7 -- . Z o 4 7 , ~ , 2 . B - , 0 9
4 7 '1.. 7 ~ - o -
t D Z V . - p - 1] X ~ O 0 (Tzs~) z (18o ore<
(~8o Gex)
By,
APPROVED m
D a t e 1 2 / 0 1 / 8 7 108935 Page
FIGURE B.6. AIRMOTOR SYSTEM CALIBPJLTION. (i of 6)
? o£ 22
108
AEDC-TR-89-6
WIDBRANGE F U E L ~
CALIBRATZONDAT&SHEETNO. 1
8ERAP~INFLABK~ELIBRATZON RJR.l, lo'l'o~. PUMP
TIME-START~ ~o :~o
8TOpt I I ' ,~# TEST NO: R8 - 2.2. RECORDED DATA
C~I,CtTZATRD
E . ' I 'D~. 8TUTI
8~OPs
i~ffJ4. ~ TEST VOLUME ~T~ (UF . ) (GaL)
. s I, 9~9"~ • • 5 i . 9 9 ~ ) . ~
1 . 0 -' , f IY~o 2 . 0 c . ~ 9 3 3
4 . 0 9 "~,q 2.
'L~BT FLOW RATE (a~)
. 3 3 # . . ~ 3 1 L
I . o 8,~ I . OBB IPE;J:~ m:]~]k
7 ~ *F"
][-FACTOR (PULSZS/GXT,).
,4 " /3 . &7 , ! - - /o . (,.z.
4 " / • , Go 4 6 ° J . & l 4,") Z . , &?,.
C~rO ~ o
~,m. I:~e,, Ss v £ e"
,;6 JLPPROVmDs
.S" 44" "
I . o &S "
I " ° 6 5 " I c e I ~ l t . D UP No ' r~ 'D o k ) ~ I A 2 . 0 4 C ,, MOTOR. ~ I S C I A & R . G E " MU/ :F / . . L r 'R - . ; r . .o ( 4 - ,'
D ~ F G L o s I ~ - D BEFOKLE k ~ X T ra.~)J. 4 . o & f " 4 . ° ~ i .'
D a t e 1 2 1 0 2 1 8 7 1 0 8 9 3 5 l ~ g e • o f 11
FIGURE B.6. AIRHOTOR SYSTEH CALIBRATION. {2 of 6)
109
A E D ~ T ~ 8 ~ 6
WIDE RANGE FUEL FLOW~TER
CAI, ZEqATION DATA B~EET BO. 3
I~O'P'~ CAX,2 ~AT'rOoKI
~'1"~'- I - Z ~ - O I
- BTARTs #1 : 3 l
STOP: # : 5'o
~ovzn vozmz. ~ ~, "7~,q
RECORDED DATA
,t) TEST FLOW RATE(GPH),
JUIB. T E M P . STARTs "70 ~ S T O P : 7 3 e F
GALLONS
PS, & K rACTOR-ZOZ0 COMPDTER I~ZW~P OUT
!~oe. ~ I ~LSZS I wxTn lSYS.-'PnZsslcAz~LA'~DIt'=,~ • ( m ) I '" I I ( " t ( " ) I ' = "==" H" "
8 I 4 - 3 0 8 9 I 9 1 4 , 7 I 7~" I -~" ] (~J.od;SJ 15 I 2-9z. f ! I -T'Ioi3 ! 7"7 / ,Y& / 9 I . ,~"0 i I
• o 2- I ~,,, ,,~ • m, ,~ qp I
I 1 3 0 I - I ~ - o ~ I ~ 9 i I ? ~ , I .~-~/- I / ~ , . . 0 2 6 1 I 1 8 o I / ~ S T ~ ( 'q'8 z o I "7~ I 4-Y I 8 , i o 8 1
A~ Po-e~su ~.E
s ~PM 6,~" Ps;. I S k? ~o tD& &o 6 6
I z o (,,7 1 8 o ~.7
o
DATA B¥8
J~n~ROVED:
~ e p e ~ r fJ ~pe~ 4 . 2 . 6 9 ~ 89918 76 "F P:.~; e,s~ &l£ P= 66 psi. /SsPH 2.7( ,97 464-2.4- 7 7 " F p-~'z PsL /IJe. p ,~ ,& Psr:
Date 12 /01 /87 108935 Page 5 o f 11 I1) DELETED-TIHE(SEC)
REVl-8-88 Z) ADDED CALC. TIRE
FIGURE S.6. AIRHOTOR SYSTEM CALIBRATION. (3 of 6)
110
AEDC-TR-89-8
RUN RUN METER DATA 2 1 COUNTS 11544.96 11547.97 METER FAC;OR - - 467.31860 467.44018 NEW METER FACTOR: 467.37939
PROVER DATA FLOW RATE 9 . 2 1 9 . 1 3
METER DATA COUNTS METER FACTOR - - NEW METER FACTOR: 4 6 7 . 3 7 9 3 9
PROVER DATA FLOW RATE
@ + U / w ~ * . , ~ * ~ : ~ : ~ $ ~ k ~ ~ ( ~ TURBINE METER TEST REPORT ~ ) ~ ] ~ . ~ k ~ ) ~ > ~ $ ~ ' X ( ~ < ,
25 JAN 88 1 2 : 2 4 METFR I D : WRFF' DATA BY:
******************************** CALIBRATION DATA ***************************
METER [IATA COUNTS - METER FACTOR - - NEW HETER FhCTOR: 4 6 7 . ~ 7 9 3 9
PROVER DATA FLOW RATE
) e + ; ~ i * ~ i ~ I ~ I ~ ~ TURBINE METER TEST REPORT ~ ~ ~ *
25 JAN 88 1 2 : 2 7 METER ID: WRFF DATA BY:
• ~ ~ ~ ~ ~ CALIBRATION DATA ~ ~ ~ ~ ~
METER DATA COUNTS METER FACTOR - - NEW METER FACTOR; 4 6 7 . 3 7 9 3 9
PROVER DATA FLOW RATE
p ovm . I A-rE" er'r'AB, Ll"r'Y'
- l e ~ ~ ~ ~ TURBINE METER TEST REPORT I ~ Z ~ * ~ ~ W
FIGURE B.6 . AIRMOTOR SYSTEM CALIBRATION. (4 o f 6)
III
AEDC-TR-89-6
******************************* CAt.ZBRATION DATA **************************
RUN METER DATA 4 COUNTS 11609.11 METER FACTOR - - 4 6 9 . 9 1 5 0 3 NEW METER FACTOR: 4 6 9 . 8 6 2 3 0
RUN RUN RUN 3 2 1
11606.51 11613.78 11600.96 469.80957 470.10400 469.58520
PROVER DATA FLOW RATE 1 6 . 2 3 1 6 . 2 8 1 6 . 3 4 16.55
RUN RUN METER DATA 2 1 COUNTS 1 1 6 7 5 . 8 5 1 1 6 7 5 , 3 4 METER FACTOR - - 4 7 2 . 6 1 6 6 9 4 7 2 . 5 9 5 9 4 NEW METER FACTOR~ 4 7 2 . 6 0 6 4 4
PROVER DATA FLOW RATE 3 3 . 4 1 3 3 . 0 2
RUN RUN METER DATA 2 1 COUNTS 11688.43 11689.21 METER FACTOR - - 473.12573 473.10747 NEW METER FACTOR: 4 7 3 , 1 4 1 6 0
PROVER DATA FLOW RATE 6 3 . 5 7 6 3 . 0 8
RUN RUN METER DATA 2 1 COUNTS 11706.08 11702.54 METER FACTOR - - 473.B4008 473.69677 NEW HETER FACTOR= 473.76855
PROVER £1ATA FLOW RATE 1 2 3 . 3 3 122 .91
RUN RUN METER DATA 2 1 COUNTS 1 1 7 1 5 . 5 7 1171B.51 METER FACTOR - - 4 7 4 . 2 2 4 1 2 4 7 4 . 3 4 3 2 6 NEW METER FACTOR: 4 7 4 , 2 8 3 6 9
PROVER DATA FLOW RATE 1 8 2 . 9 5 1 8 2 . 1 3 ************************** TURBINE METER TEST REPORT ~**~,,,~$~**,~**~
25 3AN S8 13Z07 HETER ID ! WRFF DATA BY|
~ * ~ * ~ ~ * ~ * ~ * CALIBRATION ~ATA ~ $ ~ * ~ ~ $ t ~
FIGURE B.6. AII~OTOR SYSTEM CALIBRATION. (5 o f 6)
112
AED~TR-8~8
RUN RUN HETER DATA 2 1 COU~TS 1 1 6 6 7 , 7 9 1 1 6 7 3 , 4 5 METER FACTOR - - 4 7 2 , 2 7 0 2 8 4 7 2 , 5 1 9 5 3 NEW HETER FACTOR: 4 7 2 ; 4 0 5 0 2
PROVER DATA FLOW RATE 9 , 2 1 9 , 3 3
RUN RUN METER ~ATA 2 1 COUNTS r 11678,47 1 1 6 8 0 . 9 4 METER FACTOR - - 4 7 2 , 7 2 2 4 1 4 7 2 , B 2 2 7 5 NEW HETER FACTORS 4 7 2 , 7 7 2 7 0
PROVER DATA FLOW RATE 1 7 , 6 9 1 7 , 4 4
~.5" :TA ~J #J "/'~-~=" S&-=. . I pAr,.c ~J o F 3
FIGURE B.6. AIRHOTOR SYSTEM CALIBRATION. (6 of 6)
113