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Title: Rapid-quench axially staged combustor

Patent ·
OSTI ID:872722
 [1];  [1];  [2]
  1. Niskayuna, NY
  2. Clifton Park, NY
+ Show Author Affiliations

A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.

Research Organization:
General Electric Co., Boston, MA (United States)
DOE Contract Number:
AC21-87MC23170
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
US 5996351
OSTI ID:
872722
Country of Publication:
United States
Language:
English

References (3)

Environmental aspects of low Btu gas combustion journal January 1977
Low NO/sub x/ Heavy Fuel Combustor Concept Program. Phase I. Final report report October 1981
Design and Performance of Low Heating Value Fuel Gas Turbine Combustors
  • Battista, Robert A.; Feitelberg, Alan S.; Lacey, Michael A.
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition, Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations https://doi.org/10.1115/96-GT-531
conference February 2015

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rapid-quench
axially
staged
combustor
cooperating
compressor
driving
gas
turbine
cylindrical
outer
casing
combustion
liner
upstream
rich
section
quench
downstream
lean
disposed
defining
chamber
core
region
plurality
holes
diameter
provide
cooling
jet
penetration
alternative
embodiment
middle
third
provide cooling
cylindrical outer
combustion chamber
gas turbine
alternative embodiment
core region
holes disposed
combustor casing
stream rich
combustion liner
third plurality
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