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Title: Combustor liner cooling system

Patent ·
OSTI ID:1089422
;

A combustor liner is disclosed. The combustor liner includes an upstream portion, a downstream end portion extending from the upstream portion along a generally longitudinal axis, and a cover layer associated with an inner surface of the downstream end portion. The downstream end portion includes the inner surface and an outer surface, the inner surface defining a plurality of microchannels. The downstream end portion further defines a plurality of passages extending between the inner surface and the outer surface. The plurality of microchannels are fluidly connected to the plurality of passages, and are configured to flow a cooling medium therethrough, cooling the combustor liner.

Research Organization:
General Electric Co., Schenectady, NY (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
8,499,566
Application Number:
12/855,156
OSTI ID:
1089422
Country of Publication:
United States
Language:
English

References (18)

Cooled thermal barrier coating on a turbine blade tip patent October 2002
Transpiration cooling in thermal barrier coating patent April 2002
Turbine blade tip having thermal barrier coating-formed micro cooling channels patent October 2002
Gas-turbine blade and method of manufacturing a gas-turbine blade patent June 2003
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Microfabricated rankine cycle steam turbine for power generation and methods of making the same patent February 2009
Method for making a double-wall airfoil patent June 1997
Process for creating structured porosity in thermal barrier coating patent March 2003
Fuel deoxygenation system with textured oxygen permeable membrane patent December 2008
Network cooled coated wall patent June 2005
Acoustic fuel deoxygenation system patent May 2006
Coolable wall patent October 1978
Process for forming micro cooling channels inside a thermal barrier coating system without masking material patent April 2003
Porous laminated material patent October 1981
Turbine airfoil trailing edge with micro cooling channels patent December 2002
Method and apparatus for cooling combustor liner and transition piece of a gas turbine patent March 2006

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