发明名称 |
GAS TURBINE ENGINE WITH COMPRESSOR INLET GUIDE VANE POSITIONED FOR STARTING |
摘要 |
<p>A gas turbine engine includes a compressor section, the compressor section including a variable inlet guide vane which is movable between distinct angles to control the airflow approaching the compressor section. A control is programmed to position the vane at startup of the engine to direct airflow across the compressor section. The engine includes a fan for delivering bypass air into a bypass duct positioned outwardly of a core engine including the compressor section. The position of the vane is configured to direct airflow across the compressor section while an aircraft associated with the gas turbine engine is in the air, and to increase a windmilling speed of the compressor section and the turbine rotors. A method and variable inlet vane are also disclosed.</p> |
申请公布号 |
EP2809921(A1) |
申请公布日期 |
2014.12.10 |
申请号 |
EP20130775616 |
申请日期 |
2013.01.17 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
WEHMEIER, ERIC, J. |
分类号 |
F02C7/22;F01D19/00;F02C3/13;F02C7/262;F02C9/20;F02K1/12;F02K3/06;F02K3/075 |
主分类号 |
F02C7/22 |
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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