发明名称 |
Turbine blade clearance control system |
摘要 |
Past gas turbine engines have been manufactured with a variety of systems which have attempted to compensate for the varying radial clearance or interface between a tip of a turbine blade and a surrounding shroud. Such systems have engineered in large clearances, utilized special tips on blades and provided abradable structures. The present system controls a radial clearance or an interface or spaced distance between a tip of a blade and a stationary shroud. The system includes an introduction of a cool fluid or a hot fluid flow or a combination of cool fluid and hot fluid into a support case cavity. The flow is controlled by modulating a flow control apparatus and controlling the expansion of a nozzle support case and a stationary shroud relative to the position of the tip of the turbine blade. The system improves efficiency, longevity and operation of the gas turbine engine.
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申请公布号 |
US5779436(A) |
申请公布日期 |
1998.07.14 |
申请号 |
US19960693774 |
申请日期 |
1996.08.07 |
申请人 |
SOLAR TURBINES INCORPORATED |
发明人 |
GLEZER, BORIS;BAGHERI, HAMID |
分类号 |
F01D11/10;F01D11/24;F02C7/28;(IPC1-7):F04D29/38 |
主分类号 |
F01D11/10 |
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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