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METHOD AND SYSTEM TO FACILITATE SEALING IN GAS TURBINES

United States Patent Application

20150098808
A1
View the Complete Application at the US Patent & Trademark Office
A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
Morgan, Victor John (Simpsonville, SC), Foster, Gregory Thomas (Greer, SC), Sarawate, Neelesh Nandkumar (Niskayuna, NY), Weber, David Wayne (Simpsonville, SC)
General Electric Company (Shenectady NY)
14/ 049,020
October 8, 2013
FEDERAL RESEARCH STATEMENT [0001] This invention was made with Government support under Contract No. DE-FC26-05NT42643, awarded by the Department of Energy (DOE), and the Government has certain rights in this invention.