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Title: Combustor assembly in a gas turbine engine

A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct.
Authors:
;
Publication Date:
OSTI Identifier:
1178746
Report Number(s):
9,016,066
13/718,297
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Dec 18
Research Org:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING