发明名称 |
Ceramic blade with tip seal |
摘要 |
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).
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申请公布号 |
US5653579(A) |
申请公布日期 |
1997.08.05 |
申请号 |
US19950555686 |
申请日期 |
1995.11.14 |
申请人 |
SOLAR TURBINES INCORPORATED |
发明人 |
GLEZER, BORIS;BHARDWAJ, NARENDER K.;JONES, RUSSELL B. |
分类号 |
F01D5/22;F01D11/02;F01D11/08;F16J15/32;(IPC1-7):F01D5/20 |
主分类号 |
F01D5/22 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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