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Title: Methods and systems to thermally protect fuel nozzles in combustion systems

Patent ·
OSTI ID:1111145

A method of assembling a gas turbine engine is provided. The method includes coupling a combustor in flow communication with a compressor such that the combustor receives at least some of the air discharged by the compressor. A fuel nozzle assembly is coupled to the combustor and includes at least one fuel nozzle that includes a plurality of interior surfaces, wherein a thermal barrier coating is applied across at least one of the plurality of interior surfaces to facilitate shielding the interior surfaces from combustion gases.

Research Organization:
General Electric Company, Schenectady, NY, USA
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
8,607,569
Application Number:
12/495,918
OSTI ID:
1111145
Country of Publication:
United States
Language:
English

References (12)

Smooth outer coating for combustor components and coating method therefor patent May 2008
Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein patent September 2001
Thermally protected venturi for combustor dome patent June 1993
High temperature turbine nozzle for temperature reduction by optical reflection and process for manufacturing patent August 2005
Gas turbine can annular combustor patent July 2006
Premixing burner with impingement cooled centerbody and method of cooling centerbody patent March 2006
Hybrid film cooled combustor liner patent December 2003
Method of protecting gas turbine combustor components against water erosion and hot corrosion patent April 2000
Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion patent August 2002
Air Blast Fuel Atomizer patent November 1972
Article protected by thermal barrier coating having a sintering inhibitor, and its fabrication patent November 2004
Low no.sub.x fuel nozzle assembly patent September 1997

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