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公开(公告)号：EP3354876A1
公开(公告)日：2018-08-01
申请号：EP18154161.6
申请日：2018-01-30
摘要： A gas turbine engine (10) has an engine core including a low pressure compressor (12a), a high pressure compressor (14a), a high pressure turbine (14b) and a low pressure turbine (12b) coaxially mounted about an engine axis (CL) and fluidly connected in series by a core gaspath (11). The low pressure turbine (12b) is drivingly connected to the low pressure compressor (12a) via an external shaft (12d) disposed radially outwardly of the core gaspath (11).
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公开(公告)号：EP4442982A1
公开(公告)日：2024-10-09
申请号：EP24167778.0
申请日：2024-03-28
CPC分类号： F02C7/277 , F05D2260/40620130101 , F02C7/32
摘要： An aircraft system is provided that includes a thrust rotor (22) and a powerplant (24) coupled to and configured to drive rotation of the thrust rotor (22). The powerplant (24) includes a gas turbine engine, a drivetrain (30) and a fluid motor (28). The gas turbine engine includes a rotating assembly (70), a compressor section (44), a combustor section (45), a turbine section (46) and a flowpath (42) extending through the compressor section (44), the combustor section (45) and the turbine section (46). The rotating assembly (70) includes a turbine rotor (58) in the turbine section (46). The turbine rotor (58) is configured to convert fluid power of combustion products flowing through the flowpath (42) within the turbine section (46) into mechanical power for driving rotation of the rotating assembly (70) during a mode of engine operation. The drivetrain (30) is configured to rotatably couple the fluid motor (28) to the rotating assembly (70). The fluid motor (28) is configured to boost the mechanical power for driving the rotation of the rotating assembly (70) during the mode of engine operation.
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公开(公告)号：EP4276296A1
公开(公告)日：2023-11-15
申请号：EP23173128.2
申请日：2023-05-12
发明人： VALOIS, Patrick , WIGNY, Robert
IPC分类号： F02C9/00
摘要： A method is provided for monitoring operation of an engine (14). During this method, a database is provided for a parameter of the engine (14). The database includes a plurality of values for the parameter determined over a period of time. Confidence bands are established using a probability density function on the database. An action is performed in response to a comparison of a first updated value for the parameter to the confidence bands. The engine (14) may be configured as a gas turbine engine (14) or another type of heat engine.
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公开(公告)号：EP4036392A1
公开(公告)日：2022-08-03
申请号：EP22153320.1
申请日：2022-01-25
摘要： A hybrid aircraft power plant has a gas turbine engine (10) has a high-pressure spool (25) including a high-pressure compressor (25a), a high-pressure turbine (25b), and a high-pressure shaft (25c) drivingly engaging the high-pressure turbine (25b) to the high-pressure compressor (25a), a low-pressure spool (24) including a low-pressure compressor (24a), a low-pressure turbine (24b), and a low-pressure shaft (24c) drivingly engaging the low-pressure turbine (24b) to the low-pressure compressor (24a), an electric motor (32) drivingly engaged to the low-pressure shaft (24c), and a torque-transmitting device operatively connected to the high-pressure shaft (25c) and having an engaged configuration in which the torque-transmitting device drivingly engages the electric motor (32) to the high-pressure shaft (25c) and a disengaged configuration in which the torque-transmitting device disconnects the electric motor (32) from the high-pressure shaft (25c).
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公开(公告)号：EP3859133A1
公开(公告)日：2021-08-04
申请号：EP21153424.3
申请日：2021-01-26
发明人： PLANTE, Ghislain , VALOIS, Patrick
摘要： A gas turbine engine (10; 100) having: an engine core having, in serial flow communication, a low-pressure compressor (12a), a high-pressure compressor (14a), a high-pressure turbine (14b) drivingly connected to the high-pressure compressor (14a), and a low-pressure turbine (12b) drivingly connected to an output shaft (18); and a clutch (40; 140) having a disengaged configuration in which the low-pressure turbine (12b) is drivingly disconnected from the low-pressure compressor (12a) such that, in the disengaged configuration, the clutch (40; 140) disengages the low-pressure turbine (12b) from the low-pressure compressor (12a), and an engaged configuration in which the low-pressure turbine (12b) is drivingly connected to the low-pressure compressor (12a), the low-pressure turbine (12b) drivingly connected to the output shaft (18) in both of the engaged and disengaged configurations of the clutch (40; 140).
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公开(公告)号：EP3339607B1
公开(公告)日：2020-05-13
申请号：EP17192925.0
申请日：2017-09-25
发明人： PLANTE, Ghislain , VALOIS, Patrick
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公开(公告)号：EP4155521A1
公开(公告)日：2023-03-29
申请号：EP22197878.6
申请日：2022-09-26
发明人： VALOIS, Patrick
摘要： An aircraft power plant (10) comprising: a high-pressure spool (25) including a high-pressure compressor (25A), a high-pressure turbine (25B), and a high-pressure shaft (25C) drivingly engaging the high-pressure turbine (25B) to the high-pressure compressor (25A); a low-pressure spool (24) including a low-pressure compressor (24A), a low-pressure turbine (24B), and a low-pressure shaft (24C) drivingly engaging the low-pressure turbine (24B) to the low-pressure compressor (24A); an electrical machine (50) operable as a generator; and a transmission (60) having a first input (60A) drivingly engaged by the high-pressure shaft (25C), a second input (60B) drivingly engaged by the low-pressure shaft (24C), and an output (60C) drivingly engaging the electrical machine (50), the transmission (60) having a coupling system selectively interconnecting the output (60C) with one of: the first input (60A), with the second input (60B) disconnected from the output (60C); the second input (60B), with the first input (60A) disconnected from the output (60C); and both of the first input (60A) and the second input (60B).
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公开(公告)号：EP3964700A1
公开(公告)日：2022-03-09
申请号：EP21195382.3
申请日：2021-09-07
摘要： A turboprop or turboshaft gas turbine engine (10) includes a low pressure turbine (30) drivingly engaged to an output shaft (46) for driving a rotatable load (22). A low pressure compressor (26) is de-coupled from the low pressure turbine (30), the low pressure compressor (26) and turbine (30) rotating independently from one another. A high pressure compressor (28) is disposed downstream from the low pressure compressor (26) and is in fluid communication therewith to receive pressurized air therefrom. A high pressure turbine (32) is disposed downstream from the high pressure compressor (28) and is drivingly engaged thereto via a high pressure shaft (34). The high pressure turbine (32) is disposed upstream from the low pressure turbine (30) and is in fluid communication therewith. An electric motor (36) receives power from a power source (42), is drivingly engaged to the low pressure compressor (26), and is operable to drive the low pressure compressor (26) independently from the low pressure turbine (30), the high pressure compressor (28) and the high pressure turbine (32).
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公开(公告)号：EP3354876B1
公开(公告)日：2020-04-01
申请号：EP18154161.6
申请日：2018-01-30
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公开(公告)号：EP3623600A1
公开(公告)日：2020-03-18
申请号：EP19196822.1
申请日：2019-09-11
摘要： An aircraft engine (10) has a high pressure spool (40) including a high pressure turbine (41) drivingly connected to a high pressure compressor (42). A low pressure spool (20) including a low pressure compressor (22) is fluidly connected to the high pressure compressor (42). A low pressure turbine (21) is drivingly connected to the low pressure compressor (22) to drive the low pressure compressor. A load (16) is drivingly connected to the low pressure turbine (21), the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform (30) is disclosed.
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