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Low-Emissions Gas Turbine Combustion: Design Trends and Challenges
Keith McManus GE Global Research Center Niskayuna NY MACCCR Workshop October 27-30, 2014 Boulder, CO
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Modern gas turbine combustor
Diffuser
Fuel Nozzle
Turbine Nozzle
Inner liner
Outer liner
Air swirler
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Balance reduced emissions with operability, durability, cost &weight
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CFD Modeling – GEnx TAPS
CFD is used in early scoping of design concepts
and optimization of combustor features
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Combustion Modeling - Physics
Turbulent subsonic flow potentially with large structures
Spray, atomization, vaporization and mixing
Swirling turbulent flow with phase change
Turbulent subsonic flow with reaction
Boundary layer flow with/wo mass injection
Acceleration to sonic conditions
Radiant energy transfer
Jet in reacting turbulent cross-flow
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Open Lit. Datasets Available for Use by Industry
Database Owner Flame Regime
Swirler Geom
Flame params,
P, T
Exit Params (T,NOx,… )
Cold Flow & Scalars
Reac. Flow & Scalars
Bluff body
Flames
Sydney,
Sandia
Non-
premixed
No Yes
STP
Yes Yes Yes
Swirl
Flames
Sydney,
Sandia
Non-
premixed
Axial-
tangential
Yes
STP
Yes Yes Yes
Low-swirl
Burner
LBL Premixed Axial
swirler
Yes
High P&T
Yes Yes Yes
2-D Slot
Burner
Mich. Premixed No Yes
STP
No Yes Yes
DOE-HAT
SimVal
DOE Premixed Axial
swirler
Yes
22 atm,
700 K
No Yes Yes
High Swirl
Flame
PTFWG, DOE-LBL
premixed Axial
Swirler
Yes
High P&T
Yes Yes Yes
Jet Flames Sydney,
Sandia
Partially
premixed
No Yes
STP
No Yes Yes
Vitiated
Co-flow (Augmentor)
Berkley,
Sydney
Partially
premixed
NA Yes
1 atm, 300-1080K
Yes Yes Yes
Jet in cross
Flow
Stanford Non
premixed
NA Yes
STP
No Yes No
Sydney-Sandia Flames,
//www.sandia.gov/TNF/abstra
ct.html
Strakey et al. NTEL, SimVal,
2006(http://www.netl.doe.gov/p
ublications/factsheets/rd/R&D0
99.pdf)
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Can we extrapolate data to design conditions?
Pressure, atm
Te
mp
era
ture
Alt. Relight
-40F
Sea level L/O
59F
Take-off 1000F
1500F
50 1 0.4
Cruise
Inlet Pressure and Temperature Map
20
Canonical data sets
Jet A
supercritical
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Combustion Facilities
• Experimental Capability
– High pressure, temp, flow
– Up to 800psi, 1475F
– 10+ test cells
• Build to suit combustion rigs
• Natural gas, liquid fuel
• Gas fuel blends (custom)
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Diagnostic Capabilities Mixing Velocity Flame shape Heat release
q’ Equivalence ratio f’
Gas T Surface T Spray diagnostics
•Sampling probe
•Acetone/NO PLIF
•Spray visualization
•Hotwire (u’)
•Two microphone method (u’)
•LDV
•PIV
•Video camera
•High speed camera
•Chemiluminescence imaging
•OH-PLIF (2D)
•Multi-color PMT
•Chemiluminescence imaging
•Laser absorption based on CH4
•Chemiluminescence (CH*, OH*, CO2*)
•Type-B TC
•TDLAS
•TFP, PIVT, FRS under development
•IR Pyrometer • High speed shadowgraph
• Optical patternation – spray pattern
• PDPA/Malvern – droplet size distribution, velocity
PIV – Particle Image Velocimetry
Tomographic Chemiluminescence Imaging
OH-PLIF Mixing PLIF Video & HS camera
IR Pyrometer Spray Shadowgraphy Spray Optical Patternation Mie Scattering for Spray
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Summary
• Emissions regulations are main driver for new combustion technology
• Lean-burn strategy has been adopted at GE
• TAPS design has been developed and implemented in
GEnx – 50% margin to CAEP6 NOx emissions level
• Combustion CFD and advanced diagnostics leveraged to reduce number of tests and for design screening