发明名称 |
TURBINE BLADE TIP CLEARANCE CONTROL |
摘要 |
An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising. |
申请公布号 |
EP2552780(A1) |
申请公布日期 |
2013.02.06 |
申请号 |
EP20100849131 |
申请日期 |
2010.03.31 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
JOE, CHRISTOPHER R.;WARD, DANIEL A. |
分类号 |
B64D27/00 |
主分类号 |
B64D27/00 |
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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