LOW-NOX FLAMELESS OXIDATION COMBUSTOR FOR HIGH EFFICIENCY GAS
7. Low NOx Flameless Combustion for Jet Engines and Gas Turbines, Technion, Israel
Transcript of 7. Low NOx Flameless Combustion for Jet Engines and Gas Turbines, Technion, Israel
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9th Israeli Symposium on Jet
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October 7 2010,
Technion, Istarel
www. jet-engine-lab.technion.ac.il1
"Low NOx Flameless Combustion
for Jet Engines and Gas turbines"Yeshayahou Levy
Technion - ISRAEL
http://jet-engine-lab.technion.ac.il
9th
Israeli Symposium on Jet Engines and Gas Turbines
October 7 2010, Technion, Istarel
Dr. Valery Sherbaum, Technion
Dr. Vitali Ovcherenko, Technion
Dr. Vladimir Erenburg, TechnionDr. Igor Geisinski, Technion
Mr. Josef Shemenson
, Technion
Dr. Arvind
Rao, Delft, The Netherlands
Prof. Mario Costa, IST, PortugalProf. Farid
C. Christo, The University of South, Australia
MY THANKS TO ALL CONTRIBUTORS:
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Noise (dB)Nox, CO, UHC
(%)Fuel
Consumption
(%)
Maintanance
Cost (%)
2025
2015present
0
10
20
30
40
50
60
70
80
90
100
2025
2015
present
NOx, CO & UHC emissions are to be reduced by 70% by year2015 and 80% by year 2025
Fuel Consumption & CO2
emission to be cut by 15% by year 2015
and 25% by year 2025
Anticipated Future Projections of
Engine performance
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NOx Formation in Combustor
Conventional combustion process
Primary zone (2500K)
Dilution zone (TET=1600K)
Formation (simplified) pathways:
Thermal (>1800K)
O2 2ON2 + O NO + N
N + O2 NO + O
Prompt (CH, HCN,..)
Fuel-nitrogen (bound N)
CONVENTIONAL COMBUSTOR
NOx FORMATION REGION
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T
X
400
C
2200
C
1300
C
1500
C
No NOxproduction
flameless
conventional
THE CONCEPT OF FLAMELESS GAS TURBINE
COMBUSTOR
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Flameless Combustion
Different Combustion Regimes (Milani
& Saponaro, Diluted
Combustion Technologies,IFRF Combustion Journal, 2001)
CHARACTERISTICS
Recirculation of combustion productsat high temperature (> 1000C)
Reduced oxygen concentration at the
reactance
Highly transparent flame with low
acoustic oscillation
Distributed combustion zone
Uniform temperature distribution
Reduced temperature peaks
Low adiabatic flame temperature
High concentration of CO2
& H2
O
Lower Damkhler number
Low NOx and CO emission
LARGE VOLUME
% O2
% (N2
+CO2+H2O)
Observed
Experimental
Temperature
Distribution
Plessing
et al., 1998
REGULAR FLAMELESS
FLAMELESS OXIDATION METHOD FOR NOx
REDUCTION
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October 7 2010,
Technion, Istarel
www. jet-engine-lab.technion.ac.il6
FLAMELESS COMBUSTION PRINCIPLE
Conventional Combustor
High Peak Temperature
Thin reaction zone
High TemperatureGradients
High NOx production
Gas
Air
Low NOx Combustor
Low temperature peak Distributed flame
Temperature
Uniformity
Low NOx production
Gas
Air
Texit
Texit
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FLAMELESS OXIDATION IN FURNACES AND
GAS TURBINE.
Heat extraction
Main combustion(flameless
oxidation)
Inlet Exhaust
0-5% O2
Industrial Furnace
Main
combustion
Inlet
Exhaust
14-18% O2
Gas Turbine
FLAMELESS OXIDATION IN FURNACES
?
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IMPLEMENTATION OF FLOXCOM METHOD
IN GAS TURBINES
CONVENTIONAL GAS TURBINE
GAS TURBINE WITH THE FLOXCOM COMBUSTOR
5
3
2
1
6
4
3
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INDICATIONS OF INCOMPLETE COMBUSTION
CFD SIMULATIONS
(Farid C. Christo, The University of South Australia)
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Diluting air Stirring air
A 600
MODEL OF THE COMBUSTOR SHOWING
STIRRING AND DILUTING AIR INLET HOLES
OPTIONAL AIR INLETS MODIFICATIONS
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SECTOR COMBUSTOR -
FULLY
ASSSEMBELED
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OPERATING TEST RIG AT IST, PORTUGAL
PHASE I
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www. jet-engine-lab.technion.ac.il13
COMBUSTION TESTS
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72
66
60
54
48
42
36
30
24
18
12
6
0
10 m/s
k (m2s
-2)
A22SHI
A23SHI
A24SHI
A21SHI
4
4
MEAN VELOCITY VECTORS AND TURBULENT
KINETIC ENERGY FIELDS AT THE
MEASUREMENTS AT SYMMETRY PLANE INSIDE THE COMBUSTION CHAMBER
PRIMARY ZONE
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CONTOURS OF
TEMPERATURE AND O2,
CO, NOX, HC, AND CO2 CONCENTRATIONS
MEASUREMENTS
PERFORMED ATTHE SYMMETRY
PLANE
(IST PORTUGAL)
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HIGH PRESSURE FLOXCOM TEST RIG AT
ANSALDO BARI
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EMISSION TEST DIAGRAM AT 2.5 BARS (abs.),
NO AND NO2 Vs. THE EXCESS AIR PARAMETER
0
2
4
6
8
10
12
14
16
18
20
2.5 2.7 2.9 3.1 3.3 3.5 3.7 3.9 4.1
ppm
0
200
400
600
800
1000
1200
1400
1600
1800
2000
ppm
NOx
NO
CO
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EFFECT OF GEOMETRICAL
VARIATIONS
Config.
Air inlet (total = 14 holes
2 sections)
Left inlet Right inlet
A oooooooooooo oo oooooooooooooo
B ooooooo ooooooo
C oooooooooooooo
D ooooooo
P=1 bar (abs)
Q= 4KW(24 KW complete section)
PRELIMINARY DESIGN MODIFICATIONS
Config. A: ;
;
;
NOxNOxNOxNOx
Config. B:
Config. C:
;Config. D:
0.0
2.5
5.0
7.5
10.0
12.5
15.0
17.5
0.2 0.25 0.3 0.35 0.4 0.45 0.5 0.55 0.6 0.65
20.0
92
93
94
95
96
97
98
99
100
Combustio
nefficiency(%)
NOx
(dryvolu
meppm@1
5%O2)
g
NOx
COMBUSTION EFFICIENCY
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EFFECT OF FUEL COMPOSITION
(COMBUSTION OF SYNGAS)
P=1 bar (abs)
Q= 8KW
(48 KW complete section)
94321Fuel mixture
39.27681.991100CH4
43.32418.190H2
17.50000CO2
18.7029.7931.2733.5535.80LHV (MJ/Nm3)
19231965196119561952Tad (C)
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FLOXCOM COMBUSTOR HAS LARGE STABLE OPERATIONAL
RANGE.
NOx EMISSION IS LOW AS EXPECTED.
COAND UHCARE MODERATE, DESIGN MODIFICATION IS ARE
REQUIRED
BASIC STUDY IS NEEDED TO FILL GAPS
INTERMEDIATE CONCLUSION
2nd PHASE OF THE STUDY:
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New design for
Aero-engine
Heat extraction
Main
combustionInlet
Exhaust
5-8 % O2
MODIFIED FLAMELESS COMBUSTOR WITH
INTERNAL HEAT EXCHANGER.
ADVANTEGEOUS:
COOLER FLAME
NEED FOR LOWER
RECIRCULATION RATIO
21 %
O2
Main
combustionInlet Exhaust
14-18% O2
Conventional Flameless for Gas
Turbine
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HEAT AND FLOW DIAGRAM -
MODIFIED FLAMELESS COMBUSTOR.
2 3
1
Heat exchanger
5
4
x Junction
Primary Air
Secondary Air
Inlet ExitRecirculation Zone
Main Combustion
Pre-combustion
2 3
1
Heat exchanger
5
4
x Junction
Primary Air
Inlet Exit
Main Combustion
Pre-combustion
Fuel
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THE HEAT TARNSFER MECHANISM
)(
USING OPTIMAL CONFIGURATION,
COMBUSTION TEMPERATURE MAY BE
REDUCED BY AS MUCH AS 170 C !
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www. jet-engine-lab.technion.ac.il24SINGLE JET STUDY
SINGLE JET FLAMELESS COMBUSTOR
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DIFFUSION
FLAMELESS
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CFD SIMULATIONS -
TECHNION
COMBUSTION CHAMBER WITH 16 FUEL INLET
AIR
INLET
CH4
Air
Cyclic
Surfac
e
MESH FOR 1/16
SECTOR
GASEOUSEFUEL INLETS
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TEMPERATURE DISTRIBUTION
TEMPERATURE
DISTRIBUTION
~1800K
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VELOCITY FIELD AT THE CENTER LINE
CROSS-SECTION
| | | | | | | |
0 25 50
75
mm
To outlet
CH4
inlet
Air inlet
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To outlet
Vz - VELOCITY COMPONENT'S DISTRIBUTION
RECIRCULATION REGION
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TEMPERATURE DISTRIBUTION
(NEAR NOZZLE REGION)
| | | | |
| |
0 3 6 9 12 mm
DIFFUSION REGION
FUEL ENTRAINMENT
NO mass-fraction distribution
Temperature distribution
Preliminary NO predictions
NO level
5 ppm
0
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experiment
T K
simulation
COMPARISON
CFD SIMULATIONS -
EXPERIMENT
THERE IS STILL
ROOM FOR
IMPROVEMENTS
IN THE
MODELING
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-10x10-601630-Exp. data
1.60.76x10-62.5x10-12 016802190Flux = -25kW/m21.64.4x10
-6
3.3x10-12
017602290Flux = -15kW/m2
1.646x10-68.6x10-12 019002460Adiabatic
Krecirc.NOexitCOexitTexit
, KTmax
, KRegime
COMPARISON OF SIMULATION AND
TEST RESULTS
INCORPORATION OFHEAT LOSS IN THE
MODELING IMPROVED
RESULTS
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summary
Basic modeling of the FLOXCOM combustion methodwas complete. Detailed investigation into internal mixing and enhancedwall heat transfer is currently being performed.
CFD modeling of Jet Flame configuration coupled with
experimental result seems to present an efficient tool togain practical knowledge.
Final integration stage is still needed for an engineeringflameless combustion design
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INCORPORATION OF MODIFIED COMBUSTOR
IN A TURBO-FAN ENGINE.
c
c
1
9'9' n ' pc 07'
07'
PU 2 C T 1
P
GE-90
35
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Pollutant Reduction Problem
Compromises involved withconventional combustors:
Emitted species
Flame stability
Cycle efficiency
Need for alternativecombustion conceptsLOW-EMISSION WINDOW
Wulff and Hourmouziadis, 1997
35
LOWER STABILITY LIMIT
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COMBUSTION IN HOT VITIATED AIR
Stability limits -SchematicAfter
Wunning
and Wunning, 1997
Observed Experimental
Temperature DistributionPlessing et al., 1998
Flame
Stable and safe
combustion
Uniformly
distributed
temperature
Low-NOx emission
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O2, CO2, H2O MOLE FRACTION AT THE
RECIRCULATION ZONE
0
24
68
1012
14
16
0 5 10 15 20 25
Oxygen mole fraction,%
Industrialfurnaces
Gas
turbinesII I
I
BEFORE COMBUSTION
(STIRRING AIR),
II
AFTER COMBUSTION,
CO2
,
H2
O.
IF GASES WITH LARGE
OXYGEN CONCENTRATION
ARE RECIRCULATED,HIGH ADIABATIC
TEMPERATURES ( AND
NOx) ARE OBTAINED
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Recirculation Zone
InletExit
Recirculation Zone
Primary
air
Second
arya
ir
Se
condaryair
Mixing Zone
SCHEMATIC REPRESENTATION OF THE FLUID
FLOW WITHIN THE MODIFIED COMBUSTORS
Fuel Inlet
Fuel
Inlet
Exi
t
Composite
Metallic Fins
Secondary Air
Mixing holes
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Known parameters and assumptions:Inlet air temperature T
a
Inlet mass flow rate ma
,
exit temperatures Te
100% combustion and mixing efficiency
calculated Values:
Air flow distribution: stirring air, mas,dilution air, madstirring gas, mas+mr
Temperature :
stirring gas, Tscombustion, Tc
Recirculation rate:
k
oxygen percentage in every stage of the cycle.
GLOBAL EVALUATION OF THE FLOXCOM COMBUSTORGLOBAL EVALUATION OF THE FLOXCOM COMBUSTOR
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HIGH PRESSURE FLOXCOM TEST RIG
AT ANSALDO BARI
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CROSS SECTION OF THE 360 DEGREES
MODEL OF THE FLOXCOM COMBUSTOR.
T1[ x3]
T2[ x3] [ x3]
T3
P1[ x3]
P1 - Pressure sensoresT1...T3 - Temperature Sensores
Air In Exhaust gases
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Turbo and Jet
Engine Laboratory
Technion Israel
9th Israeli Symposium on Jet
Engines and Gas Turbines,
October 7 2010,
FLOXCOM RELATIVE
PERFORMANCE
ppm NOx
..........200
100..............
0
................