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1. 发明公开

EP4306783A1 AIRCRAFT POWER PLANT WITH HYDROGEN TURBO-EXPANDER 审中-实审
公开(公告)号：EP4306783A1
公开(公告)日：2024-01-17
申请号：EP23185398.7
申请日：2023-07-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： LABRECQUE, Michel , NGUYEN, Kevin
IPC分类号： F02C3/22
摘要： A method of operating an aircraft power plant (112) includes: driving a load (16) onboard an aircraft with a combustion engine (14); heating a solid metal hydride (34) onboard the aircraft to cause hydrogen gas (26) to be released from the solid metal hydride (34); expanding the hydrogen gas (26) through a turbo-expander (38) to produce work; and using the work produced by the turbo-expander (38) to drive the load (16).

2. 发明公开

EP4194678A1 SYSTEM AND METHOD FOR SYNTHESIZING ENGINE THRUST 审中-实审
公开(公告)号：EP4194678A1
公开(公告)日：2023-06-14
申请号：EP22213263.1
申请日：2022-12-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： LABRECQUE, Michel , NGUYEN, Kevin , JOSHI, Ninad
IPC分类号： F02C9/28
摘要： A method and a system for synthesizing thrust from a turbofan engine (100) are provided. The turbofan engine (100) comprising a compressor section (14), a combustor (16), and a turbine section (18) in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine (100), a pressure of fluid at an exit of the compressor section (14) and a temperature of fluid at a location upstream of the exit of the compressor section (14) are determined. A synthesized value of thrust from the turbofan engine (100) is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine (100) is output.

3. 发明公开

EP2987987A1 LOW NOISE AEROENGINE INLET SYSTEM 有权
标题翻译： GERÄUSCHARMESFLUGZEUGTRIEBWERKEINLASSSYSTEM
公开(公告)号：EP2987987A1
公开(公告)日：2016-02-24
申请号：EP15181594.1
申请日：2015-08-19
申请人： Pratt & Whitney Canada Corp.
发明人： LABRECQUE, Michel , COUTURE-GAGNON, Vincent , ULLYOTT, Richard
IPC分类号： F02C7/042 , F02C7/045
摘要： An aeroengine has an inlet system (22) which includes a deformable wall (36,38) disposed adjacent a peripheral wall (32,34) of an inlet duct (24) and a plurality of acoustic cells (40) attached to a back side (42) in fluid communication through respective holes (41) in the deformable wall (36,38) with an inlet duct air flow (11). The deformable wall (36,38) selectively forms part of the peripheral wall (32,34) of the inlet duct (24) when in an undeployed position and selectively forms a curved profile projecting into the inlet duct (24) to reduce line-of-sight noise propagation through the inlet duct (24).
摘要翻译：航空发动机具有入口系统（22），其包括邻近入口管道（24）的周壁（32,34）设置的可变形壁（36,38）和附接到后侧的多个声学单元（40）（42）通过具有入口管道空气流（11）的可变形壁（36,38）中的相应孔（41）流体连通。当处于未部署的位置时，可变形壁（36,38）选择性地形成入口管道（24）的周壁（32,34）的一部分，并且选择性地形成突出到入口管道（24）中的弯曲轮廓，通过入口管道（24）的视线噪声传播。

4. 发明授权

EP2987986B1 LOW NOISE AEROENGINE INLET SYSTEM 有权
公开(公告)号：EP2987986B1
公开(公告)日：2020-04-15
申请号：EP15181537.0
申请日：2015-08-19
申请人： Pratt & Whitney Canada Corp.
发明人： LABRECQUE, Michel , COUTURE-GAGNON, Vincent , ULLYOTT, Richard
IPC分类号： F02C7/042 , F02C7/045 , F02C7/052

5. 发明授权

EP2987989B1 VARIABLE GEOMETRY INLET SYSTEM 有权
标题翻译：可变几何入口系统
公开(公告)号：EP2987989B1
公开(公告)日：2017-12-06
申请号：EP15181618.8
申请日：2015-08-19
申请人： Pratt & Whitney Canada Corp.
发明人： LABRECQUE, Michel , COUTURE-GAGNON, Vincent , ULLYOTT, Richard
IPC分类号： F02C7/042 , F02C7/045 , F02K3/04
CPC分类号： F02C7/045 , F01D17/143 , F02C7/042 , F02K3/025 , F02K3/04 , F05D2250/311 , F05D2250/712 , F05D2250/90 , F05D2260/96
摘要： A variable geometry inlet system (11 a) of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections (40,42) moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.

6. 发明公开

EP2987986A1 LOW NOISE AEROENGINE INLET SYSTEM 有权
标题翻译：低噪声发动机进气系统
公开(公告)号：EP2987986A1
公开(公告)日：2016-02-24
申请号：EP15181537.0
申请日：2015-08-19
申请人： Pratt & Whitney Canada Corp.
发明人： LABRECQUE, Michel , COUTURE-GAGNON, Vincent , ULLYOTT, Richard
IPC分类号： F02C7/042 , F02C7/045 , F02C7/052
摘要： An aeroengine has an inlet system (22) with a forward end with respect to a flight direction (25), a main inlet duct (24) for selectively directing a first air flow (32) from a forward main intake opening (26) to a compressor rotor (12), and a secondary inlet duct (36;44) for directing a second air flow (34;50) from a secondary intake opening (38;46) to the compressor rotor (12) only when the main inlet duct (24) is closed. A control apparatus (52) is provided for selecting the first and second air flow (32,34;50) to enter into the compressor rotor (12).
摘要翻译：航空发动机具有相对于飞行方向（25）具有前端的入口系统（22），用于选择性地将第一气流（32）从前主入口开口（26）引导至主入口管道（24）的主入口管道压缩机转子（12）和次级入口管道（36; 44），所述次级入口管道用于仅在主进口（12）处将第二空气流（34; 50）从次级吸入口（38; 46）引导至压缩机转子导管（24）关闭。提供控制装置（52）用于选择第一和第二气流（32,34; 50）以进入压缩机转子（12）。

7. 发明公开

EP4194677A1 SYSTEM AND METHOD FOR SYNTHESIZING ENGINE OUTPUT POWER 审中-实审
公开(公告)号：EP4194677A1
公开(公告)日：2023-06-14
申请号：EP22213181.5
申请日：2022-12-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： LABRECQUE, Michel , NGUYEN, Kevin , JOSHI, Ninad
IPC分类号： F02C9/28
摘要： A method and a system for synthesizing output power provided by an engine (10) are provided. The engine (10) comprising a compressor section (14), a combustor (16), and a turbine section (18) in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section (14), a temperature upstream of the exit of the compressor section (14), and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine (10) is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine (10) is output.

8. 发明授权

EP3360785B1 METHODS AND SYSTEMS FOR CONTROLLING OPERATION OF AIRCRAFT ENGINES 有权
公开(公告)号：EP3360785B1
公开(公告)日：2020-11-11
申请号：EP18155860.2
申请日：2018-02-08
申请人： Pratt & Whitney Canada Corp.
发明人： LISIO, Carmine , LABRECQUE, Michel
IPC分类号： B64D31/06 , F02C9/00

9. 发明公开

EP3360785A1 METHODS AND SYSTEMS FOR CONTROLLING OPERATION OF AIRCRAFT ENGINES 有权
公开(公告)号：EP3360785A1
公开(公告)日：2018-08-15
申请号：EP18155860.2
申请日：2018-02-08
申请人： Pratt & Whitney Canada Corp.
发明人： LISIO, Carmine , LABRECQUE, Michel
IPC分类号： B64D31/06 , F02C9/00
摘要： A method and a system for controlling operation of an engine (110) of an aircraft. A first engine power limit associated with a thrust limit for a propeller (120) coupled to the engine (110) is obtained. The first engine power limit is compared to a second engine power limit associated with a mechanical limit for the engine (110) and to a third engine power limit associated with a thermal limit for the engine (110). A maximum engine power limit is set at a lowest value of the first, second, and third engine power limits.

10. 发明公开

EP2987989A1 VARIABLE GEOMETRY INLET SYSTEM 有权
标题翻译： EINLASSSYSTEM MIT VARIABLER GEOMETRIE
公开(公告)号：EP2987989A1
公开(公告)日：2016-02-24
申请号：EP15181618.8
申请日：2015-08-19
申请人： Pratt & Whitney Canada Corp.
发明人： LABRECQUE, Michel , COUTURE-GAGNON, Vincent , ULLYOTT, Richard
IPC分类号： F02C7/042 , F02C7/045 , F02K3/04
CPC分类号： F02C7/045 , F01D17/143 , F02C7/042 , F02K3/025 , F02K3/04 , F05D2250/311 , F05D2250/712 , F05D2250/90 , F05D2260/96
摘要： A variable geometry inlet system (11 a) of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections (40,42) moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
摘要翻译：飞机发动机的可变几何入口系统（11a）包括入口管道。入口管道包括至少第一和第二部分（40,42），其可在延伸位置和缩回位置之间移动，使得入口管道限定用于选择性飞行条件的入口通道的可变轴向长度。包括声学处理可以有助于控制噪声。

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