A Triple-Flame, n+3 Generation Mixer - University of Torontogoldfinger.utias.utoronto.ca/IWACC2/IWACC2/Program_files/Mongia.pdf · Dual-annular combustors for the CFM56 and GE90 engines

A Triple-Flame, n+3 Generation Mixer

Hukam Mongia, Purdue UniversityAli Mahallati and Wajid Chishty, NRC-Institute for Aerospace Research

Presented at

The 2nd UTIAS-MITACS International Workshop on Aviation and Climate ChangeUniversity of Toronto Institute for Aerospace Studies in Toronto, Ontario, Canada, May 27-28, 2010.

15/28/2010Triple-Flame Mixer for Low-NOx & Fuel

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http://www.utias.utoronto.ca/site4.aspx

Outline of Presentation

Motivation– Lower emissions and alternative fuelsSingle annular combustors – Pre- and Low-emissions Combustors, LECDual-annular combustors for the CFM56 and GE90 enginesTwin-Annular Premixing Swirl (TAPS) technology for the CFM56 and GE90 size enginesEmissions comparisonTriple-Flame Mixer

Description and Analytical Design StatusPreliminary data from NRCC

Future Plan


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Motivation for the proposed work comes from:2009 Copenhagen UN Framework Convention on Climate Change, UNFCC)-Aviation industry agreed:

Improve fuel efficiency of the world aircraft fleet by 1.5% per yearCap aviation CO2 footprint at 2020 level50% of the 2005 CO2 level by 2050.

The challenges described well by:Ted Thrasher, ICAO’s Activities on International Aviation and Climate ChangeJohn Green, Climate change, fuel burn targets and the options and limitations facing the designer Scott Hartman, Alternative Fuels in Air Transport — From Lab to World Scale Plant Fayette Collier, Overview of the Environmentally Responsible Aviation Project Dan Bulzan, NASA Emissions Reduction and Alternative Fuel ResearchChi-Ming Lee, Technical Challenges of Low Emissions and Fuel Flexible Combustors .

Let me therefore focus on developing aviation combustion technology for:Further reducing NOx emissions for future energy efficient enginesCombustibility and increased operability with conventional & alternative fuels.


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COCO

NO NOLow-Power High-Power

NO/CO/Operability Tradeoffs in a typical rich-dome combustor

5/28/2010 4Triple-Flame Mixer for Low-NOx & Fuel

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CFM56 Combustion Technologies and Products

Single Annular CombustorsPre-LEC & Low-Emissions Comb

Dual Annular CombustorsDAC I, DAC II and DAC II+

GE 90 Combustion Technologies and Products

DAC I, DAC II and DAC II+


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Twin-Annular Premixing Swirl (TAPS) stabilized Flames technology developed for potential applications in the CFM56 and GE90 engine models.Typical values quoted.


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7

NASA GRC and GE Aviation supported the development of the CFM and GE90 TAPS technologies


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0

5

10

15

20

22 27 32 37

LTO

HC

Takeoff PR

CFM56_95

CFM56_96

CFM56_97

CFM56_TAPS

CFM56_05

20

40

60

80

100

120

140

22 24 26 28 30 32 34

LTO

CO

Takeoff PR

CFM56_95

CFM56_96

CFM56_97

CFM56_TAPS

CFM56_05

0

5

10

15

20

22 27 32 37

Ch

. Sm

oke

Takeoff PR

CFM56_95

CFM56_96

CFM56_97

CFM56_TAPS

CFM56_05

75%Reduction

75%Reduction

20

30

40

50

60

70

80

22 27 32 37

LTO

NO

x

Takeoff PR

CFM56_95

CFM56_96

CFM56_97

CFM56_TAPS

CFM56_05

CFM56_PLEC

39% reduction

49%

8

Further reduction in TAPS CO emissions would be desirable for low pressure ratio engines


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01

2

34

5

678

9

34 36 38 40 42 44

LTO

HC

Takeoff PR0

10

20

30

40

50

60

70

34 36 38 40 42 44

LTO

CO

Takeoff PR

20

30

40

50

60

70

80

90

34 36 38 40 42 44

LTO

NO

x

Takeoff PR

GE90_95

GE90_97

GE90_03

GE90_TAPS-FAR

0

2

4

6

8

10

12

34 36 38 40 42 44C

h. S

mo

ke

Takeoff PR

GE90_95

GE90_97

GE90_03

GE90_TAPS-FAR

75%

45%Reduction

85%Reduction

9

GE90 TAPS technology demonstrated significant emissions reduction compared to current technology GE90 combustion system


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(a)

(d)(c)

(b)(e)

(f)

Instantaneous Vorticity contours

Time-averaged

Time-averaged CH2O PLIF

Pilot (P) fueled

P+M fueled

Twin-Flames TAPS Mixer

Pilot

Main

PRZ

CRZ

LRZ

PRZ

Typical TAPS diagnostics data from Prof. Driscoll and his studentsShow twin flames as hypothesized for TAPS mixers


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5

10

15

20

25

30

35

40

22 27 32 37

NO

xEI

Takeoff PR

CFM56_95

CFM56_96

CFM56_97

CFM56_TAPS

CFM56_05

CFM56_PLEC

TFM-Goal

5

15

25

35

45

55

65

34 36 38 40 42 44

NO

xEI

Takeoff PR

GE90_95

GE90_97

GE90_03

GE90_TAPS

TFM-30PR

TFM-40

TFM GoalsReduce NOxEI by ~50%*Simplify fuel injectors*Reduce hot-streakingImprove operabilityIncrease fuel flexibility

*Baseline combustors areCFM56 TAPS and GE90 TAPS

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Triple-Flame Mixer“Optimized strain/vorticity /FAR distribution


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Triple-Flame Mixer with optimized strain, vorticity and distribution

Vorticity Magnitude

Axial velocity

RANS Non-reacting flow; DES/LES simulation continues

CW3%

45o-vane angles

CW30%

CW10%

CW7%

CC15%

CC20%

Direct Fuel Injection, DFI, No premixing or liquid fuel jets in cross-flow.

DFI1 & DFI2 fuel flow continuously

aa5aa4

aa3aa2

aa1

aa1, aa2 ----and aa5 are the potential air atomizing locations

1

2

3


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Takeoff: 45.7 atm, 918K, 0.0279 fuel/air ratio

0< <15000 s-1

0< <1.6

-80<u<120 m/s

Progress Variable

700<T<2600K


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0< <15000 s-1

0< <1.6

-80<u<120 m/s

Progress Variable

700<T<2600K

Cruise: 21.4 atm, 737K, 0.0287 fuel/air ratio


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u<0

Preliminary Data and current status on 2-D RANS axial velocity normalized contours

Work in progress on data and simulations including LES/DES

Axial Velocity Contours Data

P0i, Psi

Ui

iU/u

Reversed Flow

Reverse-flow


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Preliminary Data and current status on 2-D RANS Total pressure coefficient contours

Total Pressure Coefficient Contours Data

sii0

si00

PP

PPCp

P0i, Psi

Ui

Reversed Flow

Reverse-flow


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Preliminary Data and current status on 2-D RANS Static pressure coefficient contours

Static Pressure Coefficient Contours Datasii0

siss

PP

PPCp

P0i, Psi

Ui

Reversed Flow

Reverse-flow


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Axial Velocity Data 3mm downstream of mixer exit

Reversed Flow

iU/u Total Pressure Coefficient Data 3 mm downstream of mixer exit

Reversed Flow

sii0

si00

PP

PPCp

Static Pressure Coefficient Data 3 mm downstream of mixer exit

Reversed Flow

sii0

siss

PP

PPCp

Axial Vorticity Data 3 mm downstream of mixer exit

∂

∂-

r

)∂( rx

uru

r

1

Reversed Flow

r

Excellent quality data for modeling and simulation


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Axial Velocity Data 3 mm downstream of mixer exit

Reversed Flow

Design Flow Rate

Twice Design

Flow Rate

iU/u

Axisymmetric quality of axial velocity contours improves with increased airflow rate.


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Total Pressure Coefficient Data 3 mm downstream of mixer exit

Reversed Flow

Design Flow Rate

Twice Design

Flow Rate

sii0

si00

PP

PPCp

Axisymmetric quality of total pressure coefficient contours improves with increased airflow rate.


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21

Future Plan for Triple-Flame Mixer

1. Continue design optimization for cold and reacting flows

2. Design, fabrication and preliminary testing at engine relevant conditions

in collaboration with a fuel nozzle vendor and NRCC

3. Conduct comprehensive diagnostics at engine relevant conditions with

“10 kHz” PIV/PLIF, kHz Dual-Beam CARS, Spray patternation (SETScan

optical patternator) and X-Ray tomography (dense sprays)

4. Design, fabricate and test “5 lb/sec” TFM in a flame tube rig at inlet

pressure and temperature approaching 25 bar and 600oC followed by

testing on a three nozzle sector

5. Formulate and validate engineering correlations, 3-D modeling and

simulation approach for combustion technology and design community.


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Documents

A Triple-Flame, n+3 Generation Mixer - University of Torontogoldfinger.utias.utoronto.ca/IWACC2/IWACC2/Program_files/Mongia.pdf · Dual-annular combustors for the CFM56 and GE90 engines