Low-Emissions Gas Turbine Combustion: Design Trends and ... · combustion technology • Lean-burn strategy has been adopted at GE • TAPS design has been developed and implemented

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