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1. 发明公开

EP4261443A1 ACTIVELY CONTROLLED BLEED VALVE 审中-实审
公开(公告)号：EP4261443A1
公开(公告)日：2023-10-18
申请号：EP23168057.0
申请日：2023-04-14
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F16K31/00 , F16K31/126 , F16K7/17
摘要： A bleed valve (20) has a valve body (21) enclosing a valve chamber (23) defining a passageway (24) between an inlet port (25) and an outlet port (26). A panel (27) is mounted into the valve body (21). The panel (27) is deflectable under fluid pressure between a sealing position blocking the passageway (24) when the bleed valve (20) is in a close state, and a bleeding position allowing fluid flow communication between the inlet port (25) and the outlet port (26) when the bleed valve (20) is an open state. A pressure control device (30) is provided to vary a fluid pressure differential between opposite sides of the panel (27) within the valve chamber (23) and selectively open or close the bleed valve (20).

2. 发明公开

EP4202190A1 IMPELLER SHROUD ASSEMBLY AND METHOD FOR OPERATING SAME 审中-实审
公开(公告)号：EP4202190A1
公开(公告)日：2023-06-28
申请号：EP22215981.6
申请日：2022-12-22
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David , REDFORD, Timothy
IPC分类号： F01D17/02 , F01D17/14 , F01D25/24 , F01D11/20 , F01D11/00
摘要： An impeller shroud assembly (54) for a gas turbine engine (20) includes an annular impeller shroud (40) disposed about an axial centerline (30). The impeller shroud (40) includes a shroud inducer portion (56) and a shroud exducer portion (58) disposed radially outward of the shroud inducer portion (56) and extending to an outer radial end (60) of the impeller shroud (40). The shroud inducer portion (56) and the shroud exducer portion (58) defining an impeller-facing surface (62) of the impeller shroud (40). The impeller shroud (40) has a pivot point (66) defined between the shroud inducer portion (56) and the shroud exducer portion (58). The impeller shroud assembly (54) further includes a clearance control device (72) connected to the shroud exducer portion (58) of the impeller shroud (40) proximate the outer radial end (60). The clearance control device (72) is configured to pivot the shroud exducer portion (58) of the impeller shroud (40) about the pivot point (66) between a first axial position and a second axial position.

3. 发明公开

EP4098898A1 TORQUE TRANSFER COUPLING AND TOOL FOR ASSEMBLY THEREOF 审中-实审
公开(公告)号：EP4098898A1
公开(公告)日：2022-12-07
申请号：EP22176525.8
申请日：2022-05-31
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F16D3/60 , F01D25/28
摘要： A tool (70) for installing segments (44) of a coupling (30) having male and female couplers (31, 33) drivingly engaged to one another by the segments (44), the tool (70) has: a coupler-engaging section (71) engageable to a female coupler (31) of the couplers (31, 33) for radially supporting the tool (70) relative to the female coupler (31) about a rotation axis (11) of the coupling (30); and a peripheral wall (73A) secured to the coupler-engaging section (71) and extending circumferentially around the rotation axis (11), a diameter (D2) of the peripheral wall (73A) selected to allow insertion of the segments (44) between the female coupler (31) and the peripheral wall (73A), the peripheral wall (73A) defining an abutting surface against which radially inner ends (46) of the segments (44) abut during insertion of the segments (44) between the female coupler (31) and the peripheral wall (73A).

4. 发明授权

EP3133266B1 Auxiliary power unit with combined cooling of generator 有权
公开(公告)号：EP3133266B1
公开(公告)日：2018-12-12
申请号：EP16183260.5
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
IPC分类号： F02C7/14 , F02C7/18 , B64D33/08 , B64D41/00 , F02C5/00 , F02K5/00 , F01C1/22
CPC分类号： F02B63/04 , B64D33/08 , B64D41/00 , F01C1/22 , F01C21/18 , F01P1/06 , F01P5/04 , F01P5/06 , F02B37/00 , F02B53/02 , F02B53/14 , F02B63/06 , F02B67/04 , F02B2053/005 , F02C5/00 , F02C7/14 , F02C7/18 , F02K5/00 , F05D2220/50 , F05D2260/213 , Y02T10/144 , Y02T10/17 , Y02T50/53 , Y02T50/672 , Y02T50/676
摘要： An auxiliary power unit (10) for an aircraft, including an internal combustion engine (12) having a liquid coolant system, a generator (64) drivingly engaged to the internal combustion engine (12) and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine (12), a first heat exchanger (66) in fluid communication with the liquid coolant system of the internal combustion engine (12), a second heat exchanger (68) in fluid communication with the liquid coolant system of the generator (64), an exhaust duct (70) in fluid communication with air passages (66b, 68b) of the heat exchangers (66, 68), and a fan (78) received in the exhaust duct (70) and rotatable by the internal combustion engine (12) for driving a cooling air flow through the air passages (66b, 68b). The liquid coolant system of the engine (12) may be distinct from fuel and lubricating systems of the auxiliary power unit (10).

5. 发明公开

EP3128153A1 AUXILIARY POWER UNIT WITH VARIABLE SPEED RATIO 有权
标题翻译： HILFSGENERATOR MITVERÄNDERLICHEMDREHZAHLVERHÄLTNIS
公开(公告)号：EP3128153A1
公开(公告)日：2017-02-08
申请号：EP16183270.4
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： F02C6/12 , F02C7/32 , B64D41/00 , F02C7/36
CPC分类号： F02B53/14 , B64D41/00 , F02B33/40 , F02B37/10 , F02B37/24 , F02B39/10 , F02B39/12 , F02B61/06 , F02B63/04 , F02B2053/005 , F02C6/12 , F02C7/32 , F02C7/36 , F05D2220/50 , F05D2260/40 , Y02T10/144 , Y02T50/44 , Y02T50/671
摘要： An auxiliary power unit (10) for an aircraft includes a rotary intermittent internal combustion engine (12) drivingly engaged to an engine shaft (16), a turbine section having an inlet in fluid communication with an outlet of the engine(s) (12), the turbine section including at least one turbine (22, 26) compounded with the engine shaft (16), and a compressor (20) having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct (72) for providing bleed air to the aircraft, the compressor (20) having a compressor rotor connected to a compressor shaft (24), the compressor shaft (24) drivingly engaged to the engine shaft (16). The driving engagement between the compressor shaft (24) and the engine shaft (16) is configurable to provide at least two alternate speed ratios between the compressor shaft (24) and the engine shaft (16).
摘要翻译：用于飞行器的辅助动力单元（10）包括驱动地接合到发动机轴（16）的旋转间歇内燃机（12），具有与发动机（12）的出口流体连通的入口的涡轮部分），所述涡轮部分包括与所述发动机轴（16）复合的至少一个涡轮机（22,26）以及具有与所述飞行器的环境流体连通的入口的压缩机（20）和与所述飞行器的环境流体连通的出口用于向飞行器提供排放空气的排放管道（72），压缩机（20）具有连接到压缩机轴（24）的压缩机转子，压缩机轴（24）驱动地接合到发动机轴（16）。压缩机轴24和发动机轴16之间的驱动接合可配置成在压缩机轴24和发动机轴16之间提供至少两个交替的速度比。

6. 发明授权

EP2492628B1 Swirl reducing gas turbine engine recuperator 有权
标题翻译： Wirbelreduzizider Gasturbinen-Rekuperator
公开(公告)号：EP2492628B1
公开(公告)日：2016-06-01
申请号：EP12157309.1
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 , VAN DEN ENDE, Daniel
IPC分类号： F28D9/00 , F28D21/00 , F02C7/10
CPC分类号： F28D21/0003 , F02C7/08 , F02C7/10 , F02C7/143 , F28D9/0018 , F28F2250/102 , F28F2265/26 , F28F2265/30 , Y02T50/675
摘要： A gas turbine engine recuperator (30) includes exhaust passages (42) providing fluid flow communication between an exhaust inlet (50) and an exhaust outlet (52). The exhaust inlet (50) is oriented to receive exhaust flow from a turbine (18) of the engine (10) and the exhaust outlet (52) is oriented to deliver the exhaust flow to atmosphere. The exhaust passages (42) have an arcuate profile in a plane perpendicular to a central axis of the recuperator (30) to reduce a swirl of the exhaust flow. Air passages (40) in heat exchange relationship with the exhaust passages (42) and providing fluid flow communication between an air inlet (56) and an air outlet (72), sealingly engage respective plenums (26,28) of the gas turbine engine (10).
摘要翻译：燃气涡轮发动机换热器（30）包括提供排气入口（50）和排气出口（52）之间的流体流动连通的排气通道（42）。排气入口（50）被定向为接收来自发动机（10）的涡轮机（18）的排气流，并且排气出口（52）被定向成将排气流输送到大气中。排气通道（42）在垂直于换热器（30）的中心轴的平面中具有弧形轮廓，以减少排气流的漩涡。与排气通道（42）热交换关系并且提供空气入口（56）和空气出口（72）之间的流体流动连通的空气通道（40）密封地接合燃气涡轮发动机的相应气室（26,28）（10）。

7. 发明公开

EP4390063A1 EXHAUST DUCT FOR HYBRID AIRCRAFT POWERPLANT 审中-公开
公开(公告)号：EP4390063A1
公开(公告)日：2024-06-26
申请号：EP23219440.7
申请日：2023-12-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F01D15/10
CPC分类号： F05D2220/7620130101 , F01D15/10 , F02K5/00 , F05D2250/31420130101 , F01D25/30 , F02C7/36 , F02C6/206 , F05D2220/32420130101 , F02K1/52
摘要： An aircraft system (20) is provided that includes a propulsor rotor (22), an electric machine (30) and a gas turbine engine (32). The electric machine (30) is operatively coupled to and configured to drive rotation of the propulsor rotor (22). The gas turbine engine (32) is operatively coupled to and configured to drive rotation of the propulsor rotor (22). The gas turbine engine (32) includes a compressor section (60), a combustor section (61), a turbine section (62), an exhaust duct (64) and a flowpath (70) extending through the compressor section (60), the combustor section (61), the turbine section (62) and the exhaust duct (64). The exhaust duct (64) extends longitudinally along the electric machine (30). The exhaust duct (64) extends partially circumferentially about the electric machine (30) between opposing circumferential sides of the exhaust duct (64).

8. 发明公开

EP4269755A1 VARIABLE GUIDE VANE CONTROL SYSTEM 审中-实审
公开(公告)号：EP4269755A1
公开(公告)日：2023-11-01
申请号：EP23170812.4
申请日：2023-04-28
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MENHEERE, David
IPC分类号： F01D17/16
摘要： A variable guide vane control system (40) comprising an actuator (40A) and a rolling contact joint (40B). The joint includes a drive ring (50) rotatable about a drive axis (A D ) and at least one roller (60) rotatable about a roller axis (A R ) parallel to the drive axis (A D ) and drivingly connectable to a vane (30). A first flexible member (70') and a second flexible member (70") connect the drive ring (50) and the roller (60) to one another. The first flexible member (70') and the second flexible member (70") are respectively tensioned when the drive ring (50) rotates about the drive axis in a first direction (R1) and in a second direction (R2) opposite the first direction (R1).

9. 发明公开

EP4174297A1 CONNECTING ARRANGEMENT BETWEEN COMPONENTS OF AN AIRCRAFT ENGINE 审中-实审
公开(公告)号：EP4174297A1
公开(公告)日：2023-05-03
申请号：EP22204812.6
申请日：2022-10-31
申请人： Pratt & Whitney Canada Corp.
发明人： MENHEERE, David , ALECU, Daniel
IPC分类号： F02C7/32 , F02C7/36 , F02K1/04 , F01D25/24
摘要： An aircraft engine (10) comprises a casing (24) extending circumferentially around a central axis (11). A support flange (31) is secured to the casing (24, 26) and extends circumferentially around the axis (11). The support flange (31) has an inner and an outer flange face (31A, 31B). A component (22) is drivingly engaged by a shaft (21) of the engine. The component (22) has a connecting section (22A) extending around the central axis (11). The connecting section (22A) has a connecting face (22B). The inner flange face (31A) is in abutment against the connecting face (22B). A retaining ring (32) extends circumferentially around the central axis (11). The retaining ring (32) is in abutment against the outer flange face (31B) of the support flange (31). The retaining ring (32) has a coefficient of thermal expansion, which is less than that of the support flange (31).

10. 发明公开

EP4089295A1 TORQUE TRANSFER COUPLING 有权
公开(公告)号：EP4089295A1
公开(公告)日：2022-11-16
申请号：EP22173106.0
申请日：2022-05-12
申请人： PRATT & WHITNEY CANADA CORP.
发明人： SHIELDS, Mark , MENHEERE, David , KIM, Dennis
IPC分类号： F16D3/62 , F16D3/50
摘要： A coupling (30) has: a first coupler (31) rotatable about an axis (A1) and defining first connections (35A) distributed about the axis (A1); a second coupler (33) defining second connections (37A) distributed about the axis (A1), the second connections (37A) offset from the first connections (35A); and segments (44) distributed about the axis (A1) and extending radially from the first connections (35A) to the second connections (37A), a segment (44) of the segments (44) having a first end (48) engaging a first connection (35A) of the first connections (35A) and a second end (46) engaging a second connection (37A) of the second connections (37A), the first end (48) circumferentially offset from the second end (46), a face (47A) of the segment (44) abutting against a face of the first coupler (31) when the segment (44) is inserted into the first connection (35A) in a first orientation such that a penetration depth of the segment (44) into the first connection (35A) in the first orientation is less than the penetration depth in a second orientation opposite the first orientation.

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