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21. 发明公开

EP4098858A1 BI-MATERIAL JOINT FOR ENGINE 审中-实审
公开(公告)号：EP4098858A1
公开(公告)日：2022-12-07
申请号：EP22176695.9
申请日：2022-06-01
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F02C7/32 , F02K1/04
摘要： An engine bi-material joint (50) includes a first flange (48) composed of a first material defining a first coefficient of thermal expansion, and a second flange (38) composed of a second material defining a second coefficient of thermal expansion. The second material is different from the first material. An interface flange (58) is engaged with the first flange (48) and with the second flange (38). The interface flange (58) material defines a third coefficient of thermal expansion being equal to or less than the first coefficient of thermal expansion and less than the second coefficient of thermal expansion. The first coefficient of thermal expansion is less than the second coefficient of thermal expansion.

22. 发明公开

EP3839227A1 GAS TURBINE ENGINE WITH VARIABLE SPEED OUTPUT 有权
公开(公告)号：EP3839227A1
公开(公告)日：2021-06-23
申请号：EP20215796.2
申请日：2020-12-18
申请人： Pratt & Whitney Canada Corp.
发明人： MENHEERE, David , CHIAPPETTA, Santo , REDFORD, Timothy , VAN DEN ENDE, Daniel
IPC分类号： F02C3/113 , F01D17/16 , F02C6/20 , F02C9/20 , F16H37/08
摘要： A gas turbine engine (10) for an aircraft includes at least a low pressure spool (26) with a low pressure turbine shaft (24) operatively connected to at least one turbine (20), the low pressure turbine shaft (24) rotatable about an engine axis, and a low pressure compressor (12) operatively connected to a low pressure compressor shaft (32) that is independently rotatable relative to the low pressure turbine shaft (24). A differential gearbox (30; 130) has an input operatively connected to the low pressure turbine shaft (24), a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft (32) and the second output of the differential gearbox (30; 130) operatively connected to an output shaft (26) of the gas turbine engine (10). The differential gearbox (30; 130) permits the output shaft (26), the low pressure compressor shaft (32) and the low pressure turbine shaft (24) to rotate at different speeds.

23. 发明公开

EP3127817A1 AUXILIARY POWER UNIT WITH ELECTRICALLY DRIVEN COMPRESSOR 有权
标题翻译： HILFSTRIEBWERK MIT ELEKTRISCH ANGETRIEBENEM KOMPRESSOR
公开(公告)号：EP3127817A1
公开(公告)日：2017-02-08
申请号：EP16183250.6
申请日：2016-08-08
申请人： Pratt & Whitney Canada Corp.
发明人： JONES, Anthony , JULIEN, Andre , MENHEERE, David , THOMASSIN, Jean , ULLYOTT, Richard , VAN DEN ENDE, Daniel
IPC分类号： B64D41/00
CPC分类号： F02B53/14 , B64D41/00 , F02B53/04 , F02B63/04 , Y02T50/53
摘要： An auxiliary power unit (10) for an aircraft includes a rotary intermittent internal combustion engine (12), a turbine (26) having an inlet in fluid communication with an outlet of the engine (12), the turbine (26) compounded with the engine (12), a compressor (20) having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor (20) rotatable independently of the turbine (26), an electric motor (64) drivingly engaged to the compressor (20), and a transfer generator (76) drivingly engaged to the engine (12), the transfer generator (76) and the electric motor (64) being electrically connected to allow power transfer therebetween. The compressor (20) or an additional compressor (21) may be in fluid communication with the inlet of the engine (12).
摘要翻译：用于飞行器的辅助动力单元（10）包括旋转间歇内燃机（12），具有与发动机（12）的出口流体连通的入口的涡轮机（26），所述涡轮机（26）与发动机（12），具有与飞行器的环境流体连通的入口和与飞行器流体连通的出口的压缩机（20），压缩机（20）可独立于涡轮机（26）旋转，电动马达（驱动地接合到压缩机20的转子发生器76和驱动地接合到发动机12的转印发生器76，转印发生器76和电动马达64被电连接以允许它们之间的动力传递。压缩机（20）或附加压缩机（21）可以与发动机（12）的入口流体连通。

24. 发明授权

EP2492472B1 Diffusing Gas Turbine Engine Recuperator 有权
标题翻译： Diffusionsrekuperator一种用于燃气涡轮发动机
公开(公告)号：EP2492472B1
公开(公告)日：2016-05-25
申请号：EP12157317.4
申请日：2012-02-28
申请人： Pratt & Whitney Canada Corp.
发明人： ELEFTHERIOU, Andreas , MENHEERE, David , ALECU, Daniel , KARANJIA, Darius Jehangir
IPC分类号： F02C7/10 , F28D9/00 , F28F13/08
CPC分类号： F02C7/10 , F02C7/08 , F02C7/14 , F05D2220/32 , F05D2260/213 , F05D2260/96 , F28D9/0018 , F28D21/0003 , F28D2021/0026 , F28F13/08

25. 发明公开

EP2492471A3 Gas Turbine Engine Recuperator with Floating Connection 有权
标题翻译： Gasturbinenmotorrekuperator mit schwebender Verbindung
公开(公告)号：EP2492471A3
公开(公告)日：2016-05-18
申请号：EP12157320.8
申请日：2012-02-28
申请人： Pratt & Whitney Canada Corp.
发明人： ELEFTHERIOU, Andreas , MENHEERE, David , ALECU, Daniel
IPC分类号： F02C7/08 , F28F9/02 , F28F9/26 , F28F21/08 , F28D9/00 , F28D21/00
CPC分类号： F02C7/08 , F05D2220/323 , F05D2230/60 , F05D2230/642 , F28D9/0018 , F28D21/001 , F28F9/0236 , F28F9/26 , F28F21/087 , F28F2230/00 , F28F2265/26 , Y10T29/49716
摘要： A gas turbine engine recuperator (30) including a plurality of independent arcuate segments (32), each segment having an inlet connection member (58) designed to sealingly engage a plenum (28) in fluid flow communication with the compressor discharge, and an outlet connection member (74) designed to sealingly engage a plenum (26) containing the combustor (16). One of the inlet and outlet connection members (74) is a rigid member forming a rigid connection to the respective plenum (26), and the other (56) of the inlet and outlet connection members includes a flexible member (56) and forms a floating connection to the respective plenum (28), the floating connection allowing relative movement between the segment (32) and a remainder of the gas turbine engine.
摘要翻译：一种燃气涡轮发动机换热器（30），包括多个独立的弧形段（32），每个段具有入口连接构件（58），其设计成密封地接合与压缩机排放流体流动连通的气室（28）连接构件（74）设计成密封地接合包含燃烧器（16）的气室（26）。入口和出口连接构件（74）中的一个是刚性构件，其形成与相应的气室（26）的刚性连接，并且入口和出口连接构件的另一个（56）包括柔性构件（56）并形成浮动连接到相应的通风室（28），浮动连接允许段（32）和燃气涡轮发动机的其余部分之间的相对运动。

26. 发明公开

EP2492471A2 Gas Turbine Engine Recuperator with Floating Connection 有权
标题翻译：具有浮动连接的燃气轮机发动机回流换热器
公开(公告)号：EP2492471A2
公开(公告)日：2012-08-29
申请号：EP12157320.8
申请日：2012-02-28
申请人： Pratt & Whitney Canada Corp.
发明人： ELEFTHERIOU, Andreas , MENHEERE, David , ALECU, Daniel
IPC分类号： F02C7/08
CPC分类号： F02C7/08 , F05D2220/323 , F05D2230/60 , F05D2230/642 , F28D9/0018 , F28D21/001 , F28F9/0236 , F28F9/26 , F28F21/087 , F28F2230/00 , F28F2265/26 , Y10T29/49716
摘要： A gas turbine engine recuperator (30) including a plurality of independent arcuate segments (32), each segment having an inlet connection member (58) designed to sealingly engage a plenum (28) in fluid flow communication with the compressor discharge, and an outlet connection member (74) designed to sealingly engage a plenum (26) containing the combustor (16). One of the inlet and outlet connection members (74) is a rigid member forming a rigid connection to the respective plenum (26), and the other (56) of the inlet and outlet connection members includes a flexible member (56) and forms a floating connection to the respective plenum (28), the floating connection allowing relative movement between the segment (32) and a remainder of the gas turbine engine.
摘要翻译：一种燃气涡轮发动机回流换热器（30），其包括多个独立的弓形段（32），每个段具有设计成密封地接合与压缩机排气口流体连通的气室（28）的入口连接构件（58）连接构件（74），其设计成密封地接合容纳燃烧器（16）的气室（26）。入口和出口连接构件（74）中的一个是与相应的气室（26）形成刚性连接的刚性构件，并且入口和出口连接构件的另一个（56）包括柔性构件（56）并且形成（28）的浮动连接，浮动连接允许节段（32）和燃气涡轮发动机的其余部分之间的相对运动。

27. 发明公开

EP4438867A1 AIRCRAFT ENGINE HAVING TWO RADIALLY OFFSET TURBINES 审中-公开
公开(公告)号：EP4438867A1
公开(公告)日：2024-10-02
申请号：EP24164304.8
申请日：2024-03-18
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F02C3/10 , F02C3/107 , F02C7/36 , F02K3/06 , F02K3/062 , F02K3/072
摘要： An aircraft engine (10), has: a high-pressure spool (25) having a high-pressure turbine (18A) drivingly engaged to a high-pressure compressor (14A); and a low-pressure spool (26) having: a first low-pressure turbine (18B) downstream of the high-pressure turbine (18A); and a second low-pressure turbine (18C) downstream of the first low-pressure turbine (18B), one or more of the first low-pressure turbine (18B) and the second low-pressure turbine (18C) drivingly engaged to a rotatable load (12), the first low-pressure turbine (18B) and the second low-pressure turbine (18C) radially offset from one another relative to a central axis (11) of the aircraft engine (10).

28. 发明公开

EP4303405A1 VARIABLE GUIDE VANE SYSTEM 审中-实审
公开(公告)号：EP4303405A1
公开(公告)日：2024-01-10
申请号：EP23182528.2
申请日：2023-06-29
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F01D17/16 , F01D25/02
摘要： A vane system (V) for an aircraft engine (10) comprises: an inner wall (42) extending circumferentially about a duct axis (D); an outer wall (44) extending circumferentially about the duct axis (D); at least one vane (50) extending from an inner end (52) attached to the inner wall (42) to an outer end (54) rotatably connected to the outer wall (44), the outer end (54) rotatable relative to the outer wall (44) about a vane axis (V); a ring (60) extending circumferentially about the duct axis (D) radially outward of the outer wall (44) relative to the duct axis (D), the ring (60) rotatable about the duct axis (D); and at least one transmission member located radially outward of the outer wall (44) and coupling the ring (60) to the outer end (54) such that rotating the ring (60) rotates the outer end (54) about the vane axis (V).

29. 发明公开

EP4276284A1 SYSTEM AND METHOD OF ANTI-ICING INLET GUIDE VANES 审中-实审
公开(公告)号：EP4276284A1
公开(公告)日：2023-11-15
申请号：EP23172659.7
申请日：2023-05-10
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F01D9/06 , F02C7/04
摘要： An inlet guide vane assembly (20) for an aircraft engine including an array of inlet guide vanes (32) having radially inner ends (36) at a radially inner shroud (30), radially outer ends (38) at a radially outer shroud (28), and airfoils (34) extending therebetween. An internal passage (44) extends radially through the airfoil (34) from a vane air inlet at the radially inner end (36) to a vane air outlet at the radially outer end (38). The vane air inlet is in fluid communication with an inner plenum (42), disposed radially inwardly of the inlet guide vane (32) and in fluid communication with an anti-icing air source (40). The vane air outlet in fluid communication with an outer plenum (50), disposed radially outwardly of the inlet guide vane (32) and having an exhaust port (52). A vane anti-icing pathway is defined in a radially-outward direction from the inner plenum (42), through the internal passage (44) of the vane (32), and into the outer plenum (50).

30. 发明公开

EP3812553A1 FAN BLADE ANTI-ICING CONCEPT 审中-公开
公开(公告)号：EP3812553A1
公开(公告)日：2021-04-28
申请号：EP20203962.4
申请日：2020-10-26
申请人： Pratt & Whitney Canada Corp.
发明人： IVAKITCH, Richard , MENHEERE, David , STONE, Paul
IPC分类号： F01D25/02 , F02C7/047 , F01D5/18 , B64C11/20 , B64D15/00 , F04D29/58
摘要： A fan blade anti-icing system comprises a fan hub (12) and a fan blade (1) extending radially outwardly from the fan hub (12). The fan blade (1) has a base (14) and an airfoil (15) extending radially outwardly from the fan base (14). The airfoil (15) having a leading edge (17), a trailing edge (18), a convex side surface (19) between the leading and trailing edge (17, 18) and a concave side surface (20) between the leading and trailing edge (17,18). The fan blade (1) further has a radial passage (21) extending from a blade air inlet (22) in the blade base (14) in communication with a source of heated air, and a rearwardly directed passage (23) in communication with the radial passage (21) and having a blade air outlet (24) forward of the trailing edge (18) and oriented tangentially to the convex side surface (19) or concave side surface (20) of the airfoil (15).

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