发明名称 |
METHOD AND DEVICE TO AVOID TURBO INSTABILITY IN A GAS TURBINE ENGINE |
摘要 |
(A1) A turbofan engine control system is provided for managing a fan operating line. The engine (10) includes a spool having a turbine housed in a core nacelle (12). A turbofan (20) is coupled to the spool (14). A fan nacelle (34) surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area (40). A controller (50) is programmed to effectively change the nozzle exit area in response to an undesired turbofan stability margin which may result in a stall or flutter condition. In one example, the physical nozzle exit area is increased at the undesired stability condition in which the airflow into the engine creates a destabilizing pressure gradient at the inlet side of the turbofan. A turbofan pressure ratio, turbofan pressure gradient, low spool speed and throttle position are monitored to determine the undesired turbofan stability margin.
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申请公布号 |
US2009245997(A1) |
申请公布日期 |
2009.10.01 |
申请号 |
US20090442146 |
申请日期 |
2009.03.20 |
申请人 |
HURWITZ WAYNE;LEVASSEUR GLENN |
发明人 |
HURWITZ WAYNE;LEVASSEUR GLENN |
分类号 |
F01D17/14;F01D17/08;F02K3/075 |
主分类号 |
F01D17/14 |
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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