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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
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)

Low NO/sub x/ Heavy Fuel Combustor Concept Program. Phase I. Final report report October 1981
Environmental aspects of low Btu gas combustion journal January 1977
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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Related Subjects

/60/
alternative
alternative embodiment
axially
casing
chamber
combustion
combustion chamber
combustion liner
combustor
combustor casing
compressor
cooling
cooperating
core
core region
cylindrical
cylindrical outer
defining
diameter
disposed
downstream
driving
embodiment
gas
gas turbine
holes
holes disposed
jet
lean
liner
middle
outer
penetration
plurality
provide
provide cooling
quench
rapid-quench
region
rich
section
staged
stream rich
third
third plurality
turbine
upstream