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

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.
Authors:
; ; ;
Publication Date:
OSTI Identifier:
1111145
Report Number(s):
8,607,569
12/495,918
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Research Org:
General Electric Company, Schenectady, NY, USA
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS