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Ceramic blade with tip seal

United States Patent

5,653,579
August 5, 1997
View the Complete Patent at the US Patent & Trademark Office
The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc (66). A shroud assembly (100) is attached to the gas turbine engine (10) and is spaced from the plurality of blades (70) a preestablished distance forming an interface (108) therebetween. Positioned in the interface is a seal (110) having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades (70).
Glezer; Boris (Del Mar, CA), Bhardwaj; Narender K. (San Diego, CA), Jones; Russell B. (San Diego, CA)
Solar Turbines Incorporated (San Diego, CA)
08/ 555,686
November 14, 1995
"The Government of the United States of America has rights in this invention pursuant to Contract No. DE-AC21-93-MC30246 awarded by the U.S. Department of Energy."