performance test

eng_portrait Rev.2 - 10/2001 copyright by law

Siemens Demag Delaval Turbomachinery B.V.

1 Added client comments 2004-03-23 HKL GH

Description: Type 2 Performance Test Procedure Compressor LC1379

- First issue 2004-02-05 HKL GH Document no.: Rev.: Page no.:

Rev. Alterations Date By Check Auth. 10030365 1 1 / 28

Performance Test Procedure Procedure Engineering Department

TYPE 2 PERFORMANCE TEST PROCEDURE FOR A CENTRIFUGAL GAS COMPRESSOR COMPRESSOR TYPE 08MV8B SDDH ORDERNR: LC1379




Document no.: 10030365

Rev.:

1

Page no.:

2 / 28

Performance Test Procedure

Engineering Department

CONTENTS -

NOTATIONS......................................................................................................................................................... 3

INDICES ................................................................................................................................................................ 4

1 GENERAL INFORMATION ....................................................................................................................... 6

2 SPECIFIED OPERATING CONDITIONS ................................................................................................ 6

3 CONDITIONS OF TEST .............................................................................................................................. 6

4 CALCULATIONS TEST / SPECIFIED PERFORMANCE PARAMETERS. ....................................... 7

5 METHOD OF MEASUREMENT AND USED INSTRUMENTS............................................................. 9

6 COMPUTATION OF RESULTS ............................................................................................................... 10

7 TEST RUNS.................................................................................................................................................. 11

8 USED FORMULA........................................................................................................................................ 12

9 MEASURING TOLERANCES .................................................................................................................. 21

TEST SETUP....................................................................................................................................................... 24

TESTDATA SECTION 1.................................................................................................................................... 25

TESTDATA SECTION 2.................................................................................................................................... 27 Literature [1.] ANSI/ASME Power Test Code 10-1997 [2.] ISO 5167 Measurement of fluid flow by means of orifice plates, nozzles and venturi tubes inserted in

circular cross-section conduits running full. [3.] API Standard 617. Centrifugal Compressors for General Refinery Service. sixth Edition, Feb 1995. [4.] Thermodynamic properties in S.I., Department of Mech. Engineering, Stanford University by W.C. Reynolds. [5.] The polytropic analysis of centrifugal compressors, by John M. Schultz. [6.] Equation of State BWRS Fluid Thermodynamic properties for light Petroleum systems. K.E. Starling. [7.] Thermodynamic properties of R134a (1,1,1,2-Tetrafluoroethane) M.L. Huber and Mark O. Linden,

Thermophysics Division National Institute of Standards and Technology Boulder C) 80303-3328 U.S.A. [8.] Equations of State Exactly Representing the phase Behaviour of pure substances. E. Bender, Ruhr

University, Bochum, Germany. [9.] VDI 2045 part 1, Acceptance and Performance Tests on Turbo Compressors and Displacement

Compressors. Appendix: ICAAMC Correction method for the influence of Reynolds Number on the Performance of Centrifugal Compressors.

[10] BPBP Berliner Prozess Berechnungs Paket, Techische Universitat Berlin,1988. Prof. H. Knapp.





Rev.:

1

Page no.:

3 / 28



NOTATIONS Symbol Description SI Units

bi C c cp cv ck

Tip width first impeller Coefficient of discharge Specific heat Specific heat at constant pressure Specific heat at constant volume Derived inverse sp. heat at const. pressure

m - kJ/kg.K kJ/kg.K kJ/kg.K kg.°C/kJ

do Do Dimp Di Dd dp dt

Throat diameter orifice Flow measuring pipe diameter Diameter first impeller Measuring station at inlet Measuring station at discharge Differential pressure Differential temperature

m m m m m bara °C

f Fa g H

Polytropic head factor Thermal expansion coeff. at orifice Acceleration due to gravity Head; Enthalpy

- - m/s2 kJ/kg

k ln

Ratio specific heats cp/cv of a real gas Naperian (natural) logarithm

- -

m M Mm N np ns

Pol. exp. for a path on the p-t diagram Molecular weight Machine Mach number Speed Pol. exp. for a path on the p-v diagram Isentr. exp. for a path on the p-v diagram

sp v

n =kY

= c / cY

- kg/kmol - rpm - -

p P Pm Pr Pse qv qm

Pressure Power Total mech. losses (equivalent) Ext. heat losses from casing & adjoining piping Seal losses Volume flow rate Mass flow rate

bara kW kW kW kW m3/s kg/s

R Ra Rem rp s Sc t

Gas constant Absolute gas constant Machine Reynolds number Pressure ratio Entropy Enveloped area compressor casing Temperature

J/kg.K J/kmol.K - - kJ/kg.°C m2 °C





Rev.:

1

Page no.:

4 / 28



Symbol Description SI Units

T u U V v X Y Z

Absolute temperature Internal energy Blade tip speed Velocity Specific volume Compr. function of compressor process Compr. function of compressor process Compr. factor

K J/kg m/sec m/s m3/kg - - -

α αr

η µ υ ρ σ

Flow coefficient orifice Heat radiation factor Diameter ratio flowmeter Expansion factor flowmeter Linear expansion coefficient Efficiency Dynamic viscosity Kinematic viscosity Specific density Measuring tolerance

- W/(m2.°C) - - m/(mK) - Ns/m2 m2/s kg/m3

-

φ Volume flow coefficient

uD

q

imp

iv

××=

2

,

4πφ

-

Ψ Head coefficient

2/2uHp=ψ

-

INDICES

Indices Description

a abs b be c co D dyn g ge imp m Me o oil p r s se sp st t

Ambient Absolute Atmospheric Bearing Compressor-housing Coupling Pipe diameter Dynamic Gas Gearbox Impeller Mass Mechanical Orifice Oil Polytropic Radiation Isentropic Seal Specified Static Test





Rev.:

1

Page no.:

5 / 28



Indices Description tot u v i d

Total Peripheral Volume Suction conditions Discharge conditions





Rev.:

1

Page no.:

6 / 28



1 GENERAL INFORMATION A type -2- aerodynamic performance test will be conducted on a gas compressor for the Salman Oil Field.

The test will be performed at the Siemens Demag Delaval Testbed in Hengelo, according PTC-10, 1997 [1]. The compressor is equipped with a 8-stage bundle, type 08MV8B

At site the compressor will be driven by a Alstom Cyclone Gasturbine through a BHS gearbox

Overall test program:

Order Description Mechanical running test

No load string test

Type I performance test

Type II performance test

Bearing inspection

Gas Leakage test

LC1379 Main rotor x x - - x x

LC1380

Spare rotor x1) - - x x -

1) Mechanical running test will be done in Type 2 performance test setup.

This document describes the type-2 performance test of the spare rotor. 2 SPECIFIED OPERATING CONDITIONS

For the specified and guaranteed operating conditions, see the latest relevant data sheets. The guarantee point is operating case “rated”. Compressor performance characteristics are guaranteed as per API 617[3]

3 CONDITIONS OF TEST The performance curve of the compressor will be determined by a test classified as type-2 acc. ASME

PTC-10, 1997 and fully in accordance with the contract specifications including API 617, 6th edition, February 1995. [3]

The test will be carried out in a closed loop arrangement with test gas mixture of 85% CO2 and 15% R134a.

Some relevant properties of the testgas:

Description Units CO2 R134a Mixture Critical pressure bara 73.8 40.56 64.1 Critical temperature K 304.2 374.18 314.4 Mol. weight Kmol/kg 44.01 102.03 52.71

The calculations of the test results measured with the test gas mixture will be done with the equations,

given in literature [6].





Rev.:

1

Page no.:

7 / 28



4 CALCULATIONS TEST / SPECIFIED PERFORMANCE PARAMETERS. 4.1 GENERAL Type-2 tests are conducted subject to the limits of Table 3.2 of PTC10.[1] The calculated values of the test and specified parameters in the next sections are given on pages 25 thru 28. 4.1.1. Volume ratio gas at test / design conditions The polytropic exponent nd for the design gas is determined from:

( )( )

+

==

i

d

dd

ii

i

d

spdi

spidspp

pp

nxTzxTz

n

pp

n

vvn

ppnn

11

1

/1

/1.. acc. PTC-10, Eq.n0 [5.2T-7]

The polytropic exponent nt for the test gas is determined from:

+×

×= mean

sppp

mean XcM

zm

)(

134.8314η acc. PTC 10 [5. 3. 9]

[ ]meanmeant XmY

n+−

=11

acc PTC 10 [5. 3. 8]

At a test/specified speed ratio, the pressure ratio rp.t at test conditions can be derived from:

sp

t

NN [ ]

[ ]

2/1

2/11

...

1

...2/1

2/1,

,

11

Re11Re

−×××××−

× −×××××−

=×

=−

−

sp

nn

spptspispisp

corrt

nn

tpsptitit

spp

corrtp

rMTZfn

n

mrMTZfn

n

W

mW

acc. PTC-10; Eq.no. 5.3.1/2/3 The volume ratio over the compressor at test and specified conditions becomes now:

[ ] [ ]specifiedvdvitestvdvi qqqq // = = sp

np

t

np rr

=

11

acc. PTC 10 Eq.no [5.3.4] and [5.3.5]

4.1.2. Calculation of Mach number





Rev.:

1

Page no.:

8 / 28



2/12/134.8314

6034.8314

×

×××

××=

×

××=

MYTzk

ND

MYTk

UMm

i

iii

imp

i

ii

π acc. PTC-10;Eq no [5. 5 .3]

4.1.3 Calculation of Reynolds number

i

i

impimp

i

iimp

i

ibND

v

bND

vbu

m

ρµ

ππ

×

×××=

××××

=×

=6060

Re acc. PTC-10;Eq no [5. 5 .4]

4.1.4. Calculation Flow Coëfficient

232

460.

460

.. πρππρ

φ ×××

=××

=impi

m

impimp

i

m

DNq

DND

q acc. PTC-10;Eq no [5. 2T-1]





Rev.:

1

Page no.:

9 / 28



5 METHOD OF MEASUREMENT AND USED INSTRUMENTS The closed loop system will be designed and installed according ASME POWER TEST CODE PTC-10,

1997 [1] see page 24. 5.1 Mass flow The mass flow of the compressor will be measured by means of a concentric square edge orifice

according ISO 5167 [2]. 5.2 Pressures and temperatures Static pressure and temperature measuring stations at the inlet and discharge of the compressor will be

located as mentioned in chapter 4 of PTC-10 [1]. Static pressure, differential pressure and temperature measuring stations at the flow measuring device are

located as mentioned in ISO 5167-1 [2]. The temperatures will be measured by means of iron constantan (J) thermocouples. Static pressures will be measured by means of absolute pressure transducers. Differential pressures will be measured by means of differential pressure transducers. The output signals of the transducers and the thermocouples are fed into an automatic data acquisition

system. 5.3 Power at coupling The gas power at test is calculated from the mass flow and the temperature rise of the gas. The mechanical losses of the compressor will be calculated from the measured values of the temperature

rise of the oil and the amount of oil. 5.4 Speed The speed signal is taken directly from the shaft keyphasor and the output of the speed monitor is fed into

the data logging system. 5.5 Calibration Instruments will be calibrated with standards traceable to international standards. Updated certified instrument calibration sheets will be available prior to actual testing.





Rev.:

1

Page no.:

10 / 28



6 COMPUTATION OF RESULTS 6.1 Flow The suction volume of the compressor is calculated from the mass flow and the density of the gas at the

suction. The density at the inlet is calculated with the aid of the total inlet pressure and temperature. The suction volume (capacity) varies directly with the speed for conversion to specified speed.

Reynolds correction on head and efficiency will be applied acc. the correction method for the influence of Reynolds Number on the performance of a compressor between test and specified conditions, acc PTC-10,1997 para. 5.6.3.

t

sptvspv N

Nqq ×= .. [m3/hr]

6.2 Head The polytropic head at the test will be calculated from inlet- and discharge conditions, and converted to a

work-input coefficient. The polytropic head varies with the square of the speed for conversion to specified speed.

corrt

sptpspp m

N

NHH Re

2

.. ×!"#$%&

×=

[kJ/kg] 6.3 Efficiency The gas efficiency on a polytropic basis will be calculated.

corrtpspp mRe.. ×≡ ηη

6.4 Power

The gas efficiency on a polytropic basis will be used to calculate the gas power at specified conditions with capacity and polytropic head.

( ) ''()

**+, ×=

spp

sppspmspgas

HqP

.

... η

[kW]

For the shaft power, at the coupling of the compressor, mechanical losses have to be added. The

mechanical losses vary with the speed to the power 2.5.

( ) ( )P PN

Nmech sp mech tsp

t. .

.

= ×

-./

0132 2 5

[kW]

6.5 Expected error of measurements The accuracy of the direct measurement magnitudes will be: Pressure : ± 0.3 % Abs. temperature : ± 0.35°C (premium-grade thermocouple, type J calibrated condition) Speed : ± 0.1 % Test gas analysis : ± 0.25 % (molweight) The accuracy of the specified characteristics at guarantee point will be:(for details see page 26&28)





Rev.:

1

Page no.:

11 / 28



7 TEST RUNS The loop will be evaporized and filled with the test gas. Operating conditions of all points to be measured are given in the table below.

OPERATING TEST CONDITIONS

Section -1-

Section -2-

Specified speed

rpm 9800

=∧ 70%

13919

=∧ 99.4%

14700

=∧ 105%

9800

=∧ 70%

13919

=∧ 99.4%

14700

=∧ 105%

Test speed rpm 6900 9800 10350 6900 9800 10350

Test inlet Press.

bara 2 2 2 6.5 6.5 6.5

Test inlet temperature

oC 35 35 35 35 35 35

Test discharge Press.

bara 4 7.3 9 18 24.5 28

Power kW 250 500 550 350 600 700

On the 99.4% speedline 5 measuring points will be taken; maximum flow, between maximum flow and guaranteed operating point, guaranteed operating point, between guaranteed operating point and surge, surge. On the 70% & 105% speedline 3 measuring points will be taken; maximum flow, between maximum flow and surge, and surge.

Two or more trials will be made to detect surge at all speedlines of 105% ; 99.4% and 70%. A test point to indicate the minimum stable capacity shall be set as close to the surge as possible. The reliability of the determination shall be demonstrated by repeating the setting. During the stabilising interval for each test point the temperature rise and its drift can be shown on the computer screen. The time necessary for stabilising depends on the size of the machine and on the temperature. The data for the test point are gathered with 60 scans equally spread over 5 minutes i.e. one scan every 5

seconds. The duration of one scan is approx. 1 sec. (with one scan all data are gathered). The allowable temperature drift over 10 minutes is 5% of the temperature rise of the gas over the compressor. 7.2 Report Aerodynamic performance: The report will comprise the following information: - Summary and conclusions on front page - Signed measuring point data

- Hand calculation of the design point. - Converted Performance test curves showing 70%, 99.4% and 105% speed and surgeline.





Rev.:

1

Page no.:

12 / 28



8 USED FORMULA Equation of state [4] 8.1 TESTCONDITIONS 8.1.1. Barometric pressure p measuredb = ( ) N/m2

8.1.2. Orifice upstream pressure p measuredo st. ( )= N/m2

8.1.3. Diameter ratio orifice throat and measuring pipe

β = dD

o

o

-

8.1.4. Expansion factor orifice (acc. ISO 5167 )

( )stoos

o

pndp

..

435.041.01×

+−= βε

p dpo st o. + → measured values

ns o. = to be determined from equation of state.

8.1.5. Density at orifice

ρ oo st

o t o

p MT z

= ×× ×

.

..8314 34 kg/m3

toto tT .. 15.273 += K

)(. measuredt to = °C Zo = to be determined from equation of state.





Rev.:

1

Page no.:

13 / 28



8.1.6. Thermal expansion coefficient at orifice

( )[ ]F ta o o t= + −1 202λ . -

8.1.7. Discharge coefficient orifice (acc. ISO 5167)

75.065.281.2

Re10

0029.01840.00312.05959.0 456789

+−+=D

C βββ

( ) 3'2

1441 0337.010900.0 βββ LL −−+ −

where:

0'21 == LL

and:

Re

.

Do

o

m t

o o

o

o

o

V Dv

q

DD

= × =× ×

:;<<<

=>??? ×

ρ π

µρ

42

Startvalue of ReD = 1.0 x 106 ReD to be determined with the calculated value of qm.t. If the deviation between the assumed and the calculated value of ReD is less than 0.05%, the value of qm.t and ReD will be fixed. 8.1.8. Mass flow orifice (acc. ISO 5167-1)

[ ] ( ) 2/122/14. 2

41 oooatm dpdFC

q ρεπβ

×××××××−

= kg/s

8.1.9. Static inlet pressure

)(. measuredp sti = N/m2





Rev.:

1

Page no.:

14 / 28



8.1.10. Density at inlet (acc. PTC-10 5.4.2)

ii

stii zT

Mp××

×=

34.8314.ρ kg/m3

ii tT += 15.273 K

)(measuredt i = °C

=iz to be determined from equation of state. 8.1.11. Inlet volume flow

i

tmiv

qq

ρ.

. = m3/s

8.1.12. Inlet mass flow

iivtm qq ρ×= .. kg/s 8.1.13. Dynamic inlet pressure (acc. PTC-10 5.4.4)

2

2

..

421

@@@@

A

BCCCCD

E

××=

i

ividyni

D

qp πρ N/m2

8.1.14. Static discharge pressure

)(. measuredp std = N/m2





Rev.:

1

Page no.:

15 / 28



8.1.15. Density at discharge (acc. PTC-10 [5.4.2])

dd

stdd zT

Mp××

×=

34.8314.ρ kg/m3

dd tT += 15.273 K

)(measuredtd = °C

=dz to be determined from equation of state. 8.1.16. Dynamic discharge pressure (acc. PTC-10 5.4.4)

2

2

..

421

FFFF

G

HIIIIJ

K

××××=

dd

tmddynd

D

qp πρ

ρ N/m2

8.1.17. Total inlet pressure

dynistitoti ppp ... += N/m2

8.1.18. Total discharge pressure

dyndstdtotd ppp ... += N/m2

8.1.19. Pressure ratio over the compressor

totitotdp ppr .. /= N/m2

8.1.20. Isentropic exponent

i

sd

ps

In

rInn

ρρ .

= -

For ρd.s and ρi (calculated with equation of state)





Rev.:

1

Page no.:

16 / 28



8.1.21. Isentropic head

disd HHH ''. (calculated with equation of state) kJ/kg 8.1.22. Isentropic efficiency

id

isds HH

HH−−

= .η -

8.1.22a. External radial heat losses: Radiation and Convection (acc. PTC-10 [ 5.4.16])

[ ] raccr ttSP α−= kW Sc = 10.4 m2 αr = 0.14 KW/(m2.K.S) 8.1.22b. Corrected isentropic efficiency: (with Radiation and Convection heat)

)(1

1

.

)(

idtm

r

s

corrs

HHqp

−+

=

η

η -

8.1.23. Polytropic work factor (acc. PTC-10 equation [5.4T-10])

[ ]itotisdtotds

s

isd

vpvpn

nHH

f×−×

−

−=

...

.

1

-

8.1.24. Polytropic exponent (acc. PTC-10 equation [5.4T-11])

i

d

p

In

rInn

ρρ= -

8.25. Polytropic head (acc. PTC-10, [5.3.3])

itotin

n

ptp vprn

nfH ××

LMNOPQ

−×−

×=−

.

1

. 1)(1

kJ/kg





Rev.:

1

Page no.:

17 / 28



8.1.26. Polytropic efficiency (acc PTC-10 Eq.no [5.2.T-9])

)(.

.. cors

isd

tptp HH

Hηη ×

−= -

8.1.27. Mechanical losses Bearings:

oiloilvoiloiltm qdtQ ρα ×××= .. kW

α oil = 2 0. kJ/kg°C

ρ oil = 800 kg/m3

qv oil. = volume of oil flow (measured) m3/s

oildt = temperature rise oil (measured) °C Seals:

Power loss of seals will be taken from manufacturer data. 8.1.28. Gas power

Pq H

g tm t p t

p.

. .=×η

kW

8.1.29. Machine Reynolds number (acc. PTC-10, [5.5.4])

t

ii

vbND

m RSTUVW×

×××=60

Reπ

-

8.1.30. Machine Mach-number (acc. PTC-10, [5.5.3])

[ ]tiiis

i

TzRn

NDMm XY

Z[\]×××

××= 2/1.60π

-

8.1.31. Volume ratio of flow over the compressor (acc. PTC-10, [5.5.5])

[ ] [ ]t

nptdviv rqq ^_`abc=1

.. / -





Rev.:

1

Page no.:

18 / 28



8.2 SPECIFIED CONDITIONS 8.2.1. Specified inlet volume flow

qt

sptvspv N

Nqq Re.. ××=

m3/hr

8.2.2. Specified polytropic efficiency

ηηη Re.. ×= tpspp

8.2.3. Specified polytropic head

Ht

sptpspp N

NHH Re

2

.. ×de

fghi×=

kJ/kg

The factors cp.d and ck.d have been calculated with the aid of the compressor design data bank using the real gas equations for the given design gas.

dp

pdp dt

Hc jjk

lmmno ×= 1

. η kJ/KG.°C

di

dp

i

d

dk

TT

H

dtpp

c pppp

q

r

sssst

u

×

×=

log

log

. kg°C/KJ

Where didd TTdt .. −= °C

8.2.4. Specified temperature difference

spp

spp

sppsp

H

cdt

.

.

.

1η

×= °C





Rev.:

1

Page no.:

19 / 28



8.2.5. Specified pressure ratio

Ω=vw

xyz= 10.

i

dspp p

pr -

where:spspi

spspisppspk dtT

dtTHc

1log

.

... ×

+××=Ω

This formula has been derived from:

[ ]spid

idsppspkspid TT

TTHcTT |

~−

××=/

log/log .. -

8.2.6. Specified discharge pressure

spisppspd prp ... ×= N/m2

8.2.7. Specified discharge temperature

spispspd TdtT .. += K

8.2.8. Specified mass flow

spispvispm qq ... ρ×= kg/s

where:

spispi

spspispi Tz

Mp

..

.. 34.8314 ××

×=ρ kg/m3

8.2.9. Specified gas power (acc. PTC-10 [5.4.13])

spp

sppspmspg

HqP

.

... η

×= kW





Rev.:

1

Page no.:

20 / 28



8.2.10. Specified mechanical losses (acc. PTC-10 [5.6.8])

tmt

spspm P

N

NP .

5.2

. ×

= kW

8.2.11. Shaft power compressor (acc. PTC-10 [5.4.14])

spsespmspgspsh PPPP .... ++= kW

8.2.12. Specified machine Reynolds number (acc. PTC-10 [5.5.4])

sp

ispisp v

bNDm

××××

=60

Reπ

-

8.2.13. Specified machine Mach-number (acc. PTC-10 [5.5.3])

[ ] 2/1...60 spispispspsi

spisp

zTRn

NDMm

×××

××=

π -

where spi

vp

spi

ispsi Y

cc

Yk

n

=

=/

.

8.2.14. Specified polytropic exponent

spdid

idi

psp

TpZTpZ

rn

××××

=ln

ln -

8.2.15. Specified volume ratio of flow over the compressor

[ ] spnsppspvdspvi rqq1

... / = -





Rev.:

1

Page no.:

21 / 28



9 MEASURING TOLERANCES 9.1 Tolerance on mass rate of flow. For the calculated values see attached figure 4. a) Uncertainty of discharge coefficient C (ISO 5167- 8.3.3.1)

cσ = 0.6 % for β ≤ 0.6

cσ = β % for 0.6 < β ≤ 0.75 b) Uncertainty of expansion factor ε. (ISO/5167 - 8.3.3.2)

o

o

pdp×±= 4εσ %

c) Tolerance of measuring pipe diameter

( )valuemeasuredoD 0. ±=σ % d) Tolerance of throat diameter orifice plate

( )valuemeasuredod 0. ±=σ % e) Tolerance of differential pressure orifice plate

3.0. ±=odpσ %

where σdpo = uncertainty differential pressure transducer f) Tolerance of specific inlet density

( )RTipifi

σσσσ ρ ;;=

piσ = ± 0.3 %

tiσ = ± 0.35 °C

10035.0 ×±=i

Ti Tσ %

Rσ = ± 1 % for mix gas

Rσ = ± 0.5 % for pure gas

[ ] 2/1222RTipii

σσσσ ρ ++= %





Rev.:

1

Page no.:

22 / 28



g) Tolerance of mass rate of flow (ISO/5167 - 11.2.2)

2/1

2.

2.

2

2

42

2

4

422

41

41

12

12

++

−+

−

++= oodpdDcqm ρε σσσβ

σβ

βσσσ %

h) Tolerance of combined straightener (VDI 2040 Blatt 1, Abschnitt 4.4.5.4) σ str . .= ±0 5 % Tolerance on mass rate of flow

strqmqm σσσ +=

% 9.2 Tolerance on inlet volume flow

[ ] 2/122Nqmqv σσσ +±= %

9.3 Tolerance on polytropic head

( ) →−−

= iiddiip vpvpTRZn

nH .

1 . d

i

i

idp

RTf

ppH

ρρ×

−=

[ ] 2/12222TiRipipdHP

σσσσσ ρ +++= −

a) Tolerance on differential pressure compressor suction discharge

42.03.03.0 22 ±=+=− pipdσ %

b) Tolerance on suction pressure

3.0±=piσ %





Rev.:

1

Page no.:

23 / 28



c) Tolerance on gas constant

Rσ = ± 1 % for mix gas

Rσ = ± 0.5 % for pure gas d) Tolerance on suction density.

( )RTipii f σσσσ ρ ;;= %

e) Tolerance on suction temperature

10035.0 ×±=i

Ti Tσ %

f) Tolerance on discharge density

( )RTdpdd f σσσσ ρ ;;= %

3.0±=pdσ %

10035.0 ×±=d

Td Tσ %

9.4 Tolerance on gas power

( ) ( ) ttcHH dpqmidqmp −×=−= ;; σσσσ

0.1=pcσ (gas mixture), 3.0=

pcσ (pure gas) %

10035.035.0 22

×−+=−

idtitd TT

σ %

9.5 Tolerance on speed of rotation

1.0=Nσ %





Rev.:

1

Page no.:

24 / 28



TEST SETUP

Item Description T11 Suction temperature section 1 P11 Suction pressure section 1 T12 Discharge temperature section 1 P12 Discharge pressure section 1 T13 Temperature before flow orifice section 1 P13 Pressure before flow orifice section 1 PD13 Differential pressure over flow orifice section 1 T21 Suction temperature section 2 P21 Suction pressure section 2 T22 Discharge temperature section 2 P22 Discharge pressure section 2 T23 Temperature before flow orifice section 2 P23 Pressure before flow orifice section 2 PD23 Differential pressure over flow orifice section 2





Rev.:

1

Page no.:

25 / 28



TESTDATA SECTION 1 TEST DATA FOR PERFORMANCE TEST

Customer: Salman Orderno: LC1379 Type: 08MV8B

Contractor: Section 1 Operation

Description Units Specified Test Case of operation Rated Gas Composition design gas 85% CO2 / 15%R134a

Moleculair Weight Gas MW kg/kmol 25.68 52.712

Isentropic exponent ns 1.18 1.236

Polytropic exponent np 1.25 1.28

Rate of inlet volume flow qv1 am3/hr 6414 4516 Mass rate of flow m kg/hr 77707 18803

Inlet pressure pi bara 12.3 2

Inlet temperature ti °C 54 35

Inlet compressibility factor zi 0.96 0.988 Inlet density ρ kg/m3 12.10 4.16

Discharge pressure pd bara 43 7.27

Discharge temperature td °C 151.00 137.80

Discharge compressibility factor zd 0.95 0.985

Discharge density ρd kg/m3 32.96 11.379 €

Speed Ν rpm 13919 9800

Speed ratio Ντ / Νd % 0.70 Polytropic head H Kj/kg 144.60 71.82 Polytropic efficiency η % 78.2 78.2 Gaspower Pgas KW 3991.3 484

Pressure ratio rp = pd / pi 3.50 3.63

Specific volume ratio rv = vi / vd 2.722 2.733 Machine Machnumber Mm 0.793 0.798 Machine Reynoldsnumber Rem 4.265E+06 1.035E+06

Flowcoefficient φi 4.610E-01 4.610E-01 Dyn.viscosity µ kg/(s.m) 1.200E-05 1.560E-05

Specific heat factor at p=const. cpmean J/(kg.°C) - 936.1

Diameter first impeller Di mm 377

Exit tip width first impeller bi mm 15.4 Compressibility function [5] (X1+X2)/2 0.052 Compressibility function [5] (Y1+Y2)/2 1.0119

Reyn.corr.factorPTC-10 on Qv % 1.000

Reyn.corr.factorPTC-10 on Hpol % 1.008

Reyn.corr.factorPTC-10 on Ethapol.t % 1.008





Rev.:

1

Page no.:

26 / 28



Description Units PTC-10 Limits Test

Specific volume ratio rv.t / rv.sp 0.95<--->1.05 1.00

Machine Mach number ratio Mm.t - Mm.sp acc.PTC-10-1997 -0.06< >+0.08 0.005

Machine Reynolds number ratio Rem.t/Rem.sp acc.PTC-10-1997 0.10 : 20 0.243

Flowcoefficient ratio φt /φsp 0.96<--->1.04 1.000

MEASURING TOLERANCES FOR PERFORMANCE TEST Customer: Salman Orderno: LC1379

Type: 08MV8B Contractor: Stage: 1

Operation Description Units Tolerance +/- Unit

Inlet/discharge pressure p bara 0.3 % Inlet/discharge temperature t °C 0.35 °C

Upstream pressure orifice p bara 0.3 %

Differential pressure orifice dp mbar 0.3 %

Orifice temperature t °C 0.35 °C

Section 1:

Rate of mass flow m kg/hr 0.92 %

Rate of inlet volume flow qv1 am3/hr 0.93 % Polytropic Head H kJ/kg 0.7 % Power P kW 0.99 % €





Rev.:

1

Page no.:

27 / 28



TESTDATA SECTION 2 TEST DATA FOR PERFORMANCE TEST

Customer: Salman Orderno: LC1379 Type: 08MV8B

Contractor: Section 2 Operation

Description Units Specified Test Case of operation Rated Gas Composition design gas 85% CO2 / 15%R134a

Moleculair Weight Gas MW kg/kmol 25.76 52.712

Isentropic exponent ns 1.21 1.266

Polytropic exponent np 1.41 1.40

Rate of inlet volume flow qv1 am3/hr 1703 1199.00 Mass rate of flow m kg/hr 74075 16684

Inlet pressure pi bara 40.5 6.5

Inlet temperature ti °C 58.5 35

Inlet compressibility factor zi 0.87 0.961 Inlet density ρ kg/m3 43.49 13.92

Discharge pressure pd bara 153.7 24.48

Discharge temperature td °C 181.00 173.43

Discharge compressibility factor zd 0.94 0.966

Discharge density ρd kg/m3 111.55 35.97 €

Speed Ν rpm 13919 9800

Speed ratio Ντ / Νd % 0.70 Polytropic head H Kj/kg 149.30 75.32 Polytropic efficiency η % 60.7 60.7 Gaspower Pgas KW 5061 580

Pressure ratio rp = pd / pi 3.80 3.77

Specific volume ratio rv = vi / vd 2.575 2.585 Machine Machnumber Mm 0.877 0.87 Machine Reynoldsnumber Rem 7.469E+06 1.685E+06

Flowcoefficient φi 1.220E-01 1.220E-01 Dyn.viscosity µ kg/(s.m) 1.200E-05 1.528E-05

Specific heat factor at p=const. cpmean J/(kg.°C) - 985.6

Diameter first impeller Di mm 404

Exit tip width first impeller bi mm 7 Compressibility function [5] (X1+X2)/2 0.155 Compressibility function [5] (Y1+Y2)/2 1.0372

Reyn.corr.factorPTC-10 on Qv % 1.000

Reyn.corr.factorPTC-10 on Hpol % 1.0079

Reyn.corr.factorPTC-10 on Ethapol.t % 1.0079





Rev.:

1

Page no.:

28 / 28



Description Units PTC-10 Limits Test

Specific volume ratio rv.t / rv.sp 0.95<--->1.05 1.00

Machine Mach number ratio Mm.t - Mm.sp acc.PTC-10-1997 -0.04 >+0.07 -0.007

Machine Reynolds number ratio Rem.t/Rem.sp acc.PTC-10-1997 0.10 : 20 0.226

Flowcoefficient ratio φt /φsp 0.96<--->1.04 1.000

MEASURING TOLERANCES FOR PERFORMANCE TEST Customer: Salman Orderno: LC1379

Type: 08MV8B Contractor: Stage: 2

Operation Description Units Tolerance +/- Unit

Inlet/discharge pressure p bara 0.3 % Inlet/discharge temperature t °C 0.35 °C

Upstream pressure orifice p bara 0.3 %

Differential pressure orifice dp mbar 0.3 %

Orifice temperature t °C 0.35 °C

Section 2:

Rate of mass flow m kg/hr 0.70 %

Rate of inlet volume flow qv1 am3/hr 0.71 % Polytropic Head H Kj/kg 0.7 % Power P KW 0.80 % €

performance test

Documents

Transcript of performance test