Invention Grant
- Patent Title: Gas turbine support element permitting thermal expansion between combustor shell and rotor cover at turbine inlet
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Application No.: US14254985Application Date: 2014-04-17
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Publication No.: US09708920B2Publication Date: 2017-07-18
- Inventor: Remigi Tschuor , Sinisa Narancic , Guenter Filkorn
- Applicant: ALSTOM Technology Ltd
- Applicant Address: CH Baden
- Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
- Current Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
- Current Assignee Address: CH Baden
- Agency: GE Global Patent Operations
- Agent Marc A. Vivenzio
- Priority: EP11186387 20111024
- Main IPC: F23R3/60
- IPC: F23R3/60 ; F01D9/02 ; F02C7/20 ; F01D25/28 ; F23R3/00

Abstract:
A gas turbine includes a compressor, an annular combustion chamber, and a turbine, a combustion chamber shell of the combustion chamber adjoining the turbine inlet in a transition region in order to introduce the hot gases generated in the combustion chamber into the downstream turbine such that a thermal expansion-induced relative movement between the combustion chamber and the turbine inlet is possible. Combustion chamber shell support elements distributed on the periphery come into contact with a conical contour on the shaft cover due to the thermal expansion that occurs during operation and are supported on said contour. An improvement with respect to loading and service life is achieved in that the conical contour and the machine axis form an angle that allows the combustion chamber shell support elements to slide onto the conical contour.
Public/Granted literature
- US20140223921A1 GAS TURBINE Public/Granted day:2014-08-14
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