发明名称 |
Engine having power bus fault short circuit control with a disconnection switch |
摘要 |
An aircraft electrical system comprises a generator to be driven as part of a gas turbine engine. The generator supplies electrical power to a plurality of accessories associated with the gas turbine engine, and to an aircraft power bus in parallel to the supply to the accessories. A control detects a short circuit on the aircraft power bus. When a short circuit is detected on the aircraft power bus, a switch is driven open to disconnect the aircraft power bus from the generator. In this manner, the power will continue to be delivered to the plurality of accessories. In a separate feature, a control voltage is provided by an auxiliary permanent magnet generator to a voltage regulator for the main generator. |
申请公布号 |
US8213136(B2) |
申请公布日期 |
2012.07.03 |
申请号 |
US20070839763 |
申请日期 |
2007.08.16 |
申请人 |
MADDALI VIJAY K.;ROZMAN GREGORY I.;DOOLEY KEVIN;PRATT & WHITNEY CANADA CORP.;HAMILTON SUNDSTRAND CORPORATION |
发明人 |
MADDALI VIJAY K.;ROZMAN GREGORY I.;DOOLEY KEVIN |
分类号 |
H02H7/06;B64D41/00;H02H3/08 |
主分类号 |
H02H7/06 |
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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