公开(公告)号：EP3941830B1

公开(公告)日：2024-11-06

申请号：EP19920049.4

申请日：2019-12-06

发明人： LATULIPE, Eric ,  THOMASSIN, Jean ,  WANG, Xi ,  DUBREUIL, Jean ,  DIONNE, Luc ,  JULIEN, Andre

IPC分类号： B64D35/08 ,  F02B37/10 ,  F02B39/06 ,  F02B39/10 ,  H02K7/116 ,  H02K7/18 ,  B64D27/33 ,  B64D35/023 ,  B64D35/024 ,  B64D35/025

公开(公告)号：EP4446232A1

公开(公告)日：2024-10-16

申请号：EP24153732.3

申请日：2024-01-24

申请人： Airbus Helicopters

发明人： KRIER, Bernard ,  CHASSAGNE, Ivan

IPC分类号： B64D31/06 ,  B64C27/04 ,  B64D35/08 ,  F02C6/20 ,  F02C9/44 ,  B64C27/12

摘要： La présente invention concerne un procédé de pilotage d'un aéronef (1) ayant au moins deux moteurs (10) brûlant du combustible et une chaîne de transmission (25) connectée à une voilure tournante (5), chaque moteur (10) ayant un arbre de puissance (20) connecté à la chaîne de transmission (25). Une phase à économie d'énergie comprend au moins une période économique (STPASY) comprenant une régulation avec un système de régulation (55) d'un moteur actif parmi les au moins deux moteurs (10) à un régime actif ainsi qu'un arrêt ou une régulation avec le système de régulation (55) à un régime de repos de chaque moteur non actif parmi les au moins deux moteurs (10) qui n'est pas le moteur actif.

公开(公告)号：EP4414268A1

公开(公告)日：2024-08-14

申请号：EP23156399.0

申请日：2023-02-13

申请人： Hamilton Sundstrand Corporation

发明人： TATE, David James

IPC分类号： B64D27/24 ,  B64D35/00 ,  B64D35/02 ,  B64D27/02

CPC分类号： B64D27/24 ,  B64D35/00 ,  B64D35/02 ,  B64D27/026

摘要： A power system for an aircraft comprises: a motor-generator component; a shaft, wherein the motor-generator component is connectable to the shaft, the shaft connectable to an additional component of the aircraft to for torque transfer with the additional component; and a de-coupler operable to disconnect the motor-generator component from the shaft, wherein the motor-generator component is located between the de-coupler and the additional component in use.

公开(公告)号：EP4368514A3

公开(公告)日：2024-07-10

申请号：EP24162463.4

申请日：2022-09-07

申请人： PRATT & WHITNEY CANADA CORP.

发明人： BEAUCHESNE-MARTEL, Philippe ,  BIBOR, Olivier

IPC分类号： F02C9/42 ,  B64D35/08 ,  B64D31/06 ,  B64C27/12 ,  B64C27/06

CPC分类号： B64D31/06 ,  B64C27/06 ,  F02C9/42 ,  B64C27/12 ,  B64D35/08

摘要： In an asymmetric operating regime, a first engine (102) is operating in an active mode to provide motive power to an aircraft (100) while a second engine (104) is operating in a standby mode and de-clutched from a gearbox of the aircraft (100). In response to an emergency exit request, the second engine's speed is increased, at a maximum permissible rate, to a re-clutching speed while increasing the first engine's power output at a maximum permissible rate. When the re-clutching speed is reached, the second engine's power output is increased at a maximum permissible rate. In response to a normal exit request, the second engine's speed is increased to the re-clutching speed at a rate lower than the maximum permissible rate. When the re-clutching speed is reached, the second engine's power output is increased at a rate lower than the maximum permissible rate.

公开(公告)号：EP4389607A1

公开(公告)日：2024-06-26

申请号：EP23219889.5

申请日：2023-12-22

申请人： PRATT & WHITNEY CANADA CORP.

发明人： WEAVER, Paul ,  CHATELOIS, Bruno

IPC分类号： B64D27/33 ,  B64D35/025 ,  B64D27/31 ,  B64D35/08

CPC分类号： B64D27/33 ,  B64D35/025 ,  B64D27/31 ,  B64D35/08

摘要： An aircraft system (20) includes a propulsor rotor (28), a geartrain (76), a thermal engine (30), a drivetrain (78) and an electric machine (32). The geartrain (76) includes a a first power input (81) a second power input (82) and apower output (80) coupled to the propulsor rotor (28). The thermal engine (30) is configured to drive rotation of the propulsor rotor (28) through the geartrain (76). The thermal engine (30) is coupled to the first power input (81). The drivetrain (78) includes a first driveshaft (86) and a second driveshaft (87). The first driveshaft (86) is coupled to and between the second power input (82) and the second driveshaft (87). The second driveshaft (87) is angularly offset from the first driveshaft (86). The electric machine (32) is configured to drive rotation of the propulsor rotor (28) through the drivetrain (78) and the geartrain (76). The second driveshaft (87) is coupled to and between the first driveshaft (86) and the electric machine (32).

公开(公告)号：EP4082916B1

公开(公告)日：2024-05-01

申请号：EP22159632.3

申请日：2022-03-02

IPC分类号： B64D35/08

CPC分类号： B64D35/08 ,  B64D27/026

公开(公告)号：EP4238871B1

公开(公告)日：2024-04-17

申请号：EP23154928.8

申请日：2023-02-03

IPC分类号： B64D27/24 ,  B64D35/02 ,  H02P27/06 ,  B64D31/00

CPC分类号： H02P27/06 ,  B64D27/24 ,  B64D35/02 ,  H02P2209/0120130101 ,  H02P2201/0720130101 ,  B64D31/00 ,  Y02T50/60

公开(公告)号：EP4324744A3

公开(公告)日：2024-03-27

申请号：EP23192259.2

申请日：2023-08-18

申请人： Ampaire, Inc.

发明人： SPITZER, Jeffrey

IPC分类号： B64D27/02 ,  B64D27/24 ,  B64D35/024 ,  B64D35/025

摘要： Systems and methods for controlling flight via a parallel hybrid aircraft having an electric propulsion system and a combustion propulsion system are disclosed. Exemplary implementations may include: a combustion propulsion system including a combustion engine; an electric propulsion system including a motor and an electric power source, wherein the motor comprises a stator, a rotor coupled to the engine shaft, and support bearings between the rotor and the stator; a mechanical link coupled to the stator and the combustion engine, wherein the mechanical link substantially prevents movement of the stator in a rotational degree of freedom; and a propeller coupled to the engine shaft, wherein the rotor is coupled to the engine shaft between the propeller and the combustion engine.

公开(公告)号：EP4339095A1

公开(公告)日：2024-03-20

申请号：EP23197536.8

申请日：2023-09-14

申请人： PRATT & WHITNEY CANADA CORP.

发明人： KESEK, Mateusz ,  ROZPUTYNSKI, Tomasz

IPC分类号： B64C11/02 ,  B64D35/00

摘要： A propeller shaft assembly (20) for an aircraft engine (10) includes a shaft (22) having: an annular wall (32) extending circumferentially about a shaft axis (X) and circumscribing a hollowed interior (25H) defining a cavity (25) in a front end portion (23) of the shaft (22), the annular wall (32) having an outer surface (26) and an inner surface (33) facing radially inwardly to the cavity (25); and a front flange (27) projecting radially outwardly from the annular wall (32). The front flange (27) includes a hub side surface (28) defining an interface plane (P1) and adapted to abut with a propeller hub (18). The shaft (22) also includes a reinforcement web (40) defining an end wall (41) of the cavity (25), the reinforcement web (40) extending radially inwardly from the inner surface (33) of the annular wall (32). At least part of the reinforcement web (40) is radially aligned with the front flange (27). At least one perforation (PP) extends axially through the reinforcement web (40).

公开(公告)号：EP4339093A1

公开(公告)日：2024-03-20

申请号：EP23197262.1

申请日：2023-09-13

申请人： Pratt & Whitney Canada Corp.

发明人： KESEK, Mateusz ,  ROZPUTYNSKI, Tomasz

IPC分类号： B64C11/02 ,  B63H23/34 ,  B64D35/00 ,  F01D5/02

摘要： A propeller shaft assembly (20) for an aircraft engine (10) includes a shaft (22) having a bore (25) extending through the shaft (22) at a front end (24) thereof, the front end (24) of the shaft (22) having an outer surface (26) facing radially outwardly from the shaft (22) and an inner surface (33) spaced apart from the outer surface (26) and facing radially inwardly to the bore (25). The shaft (22) has a front flange (27) extending radially outwardly on the outer surface (26), the front flange (27) having a base (31) merging with the outer surface (26) of the shaft (22). A sleeve (40) is coupled to the shaft (22) within the bore (25) by an interference fit between the sleeve (40) and the shaft (22), at least part of the sleeve (40) axially aligned with the front flange (27). The sleeve (40) axially extends from a front to a rear sleeve end (41, 42), the rear sleeve end (42) axially offset from the engine side surface (29) of the front flange (27) at the base (31) of the front flange (27).