公开(公告)号：US11939925B2

公开(公告)日：2024-03-26

申请号：US17840715

申请日：2022-06-15

申请人： Raytheon Technologies Corporation

发明人： Charles E. Lents ,  Joseph B. Staubach ,  Larry W. Hardin ,  Jonathan Rheaume

IPC分类号： F02C7/36 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  F01D15/10 ,  F02C6/14 ,  F02C9/50 ,  B64D27/02

CPC分类号： F02C7/36 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  F01D15/10 ,  F02C6/14 ,  F02C9/50 ,  B64D2027/026 ,  F05D2220/76 ,  Y10S903/905 ,  Y10S903/906

摘要： A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.

公开(公告)号：US20220349351A1

公开(公告)日：2022-11-03

申请号：US17840715

申请日：2022-06-15

申请人： Raytheon Technologies Corporation

发明人： Charles E. Lents ,  Joseph B. Staubach ,  Larry W. Hardin ,  Jonathan Rheaume

IPC分类号： F02C7/36 ,  F01D15/10 ,  B64D31/06 ,  F02C6/14 ,  F02C9/50 ,  B64D27/24 ,  B64D27/10

摘要： A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.