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1.发明申请
公开(公告)号：WO2018144080A8
公开(公告)日：2018-08-09
申请号：PCT/US2017/056849
申请日：2017-10-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： HURT, Matthew, John , CARITA, Robert, Gregory , BRINSON, Thomas, Edward , CERNY, Matthew, Robert , MISRA MARTINEZ, Amit, Kumar , PARKER, David, Vickery , PEREZ VALADEZ, Alejandro, Yatzail
Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.
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2.发明申请
公开(公告)号：WO2018144080A1
公开(公告)日：2018-08-09
申请号：PCT/US2017/056849
申请日：2017-10-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： HURT, Matthew, John , PEREZ VALADEZ, Alejandro, Yatzail , BRINSON, Thomas, Edward , CERNY, Matthew, Robert , MISRA MARTINEZ, Amit, Kumar , PARKER, David, Vickery , CARITA, Robert, Gregory
Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.
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