Combustor assembly in a gas turbine engine
Patent
·
OSTI ID:1178746
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.
- Research Organization:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Number(s):
- 9,016,066
- Application Number:
- 13/718,297
- OSTI ID:
- 1178746
- Country of Publication:
- United States
- Language:
- English
Similar Records
Combustor assembly in a gas turbine engine
Gas turbine annular combustor
Axial flow gas turbine engine combustor
Patent
·
Mon Feb 18 23:00:00 EST 2013
·
OSTI ID:1082947
Gas turbine annular combustor
Patent
·
Tue May 19 00:00:00 EDT 1992
·
OSTI ID:5052451
Axial flow gas turbine engine combustor
Patent
·
Mon Feb 18 23:00:00 EST 1991
·
OSTI ID:5778011