公开(公告)号：US20170267370A1

公开(公告)日：2017-09-21

申请号：US15616187

申请日：2017-06-07

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard ULLYOTT ,  Anthony JONES ,  Andre JULIEN ,  Jean THOMASSIN

IPC: B64D41/00 ,  F02C3/10 ,  H02K7/18

CPC classification number: B64D41/00 ,  B64D2013/0611 ,  F01C1/22 ,  F01C11/008 ,  F02C3/10 ,  H02K7/1815 ,  H02K7/1823 ,  Y02T50/44 ,  Y02T50/53

Abstract: An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

公开(公告)号：US20170218783A1

公开(公告)日：2017-08-03

申请号：US15010634

申请日：2016-01-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN ,  Marie-Claude VALLIERES ,  Mike FONTAINE ,  Andre JULIEN ,  John PERERA

IPC: F01D9/04 ,  F01D5/12 ,  F01D5/02 ,  F02B37/00 ,  F02B53/08

CPC classification number: F01D9/041 ,  F01D1/026 ,  F01D5/02 ,  F01D5/12 ,  F01D17/12 ,  F02B37/00 ,  F02B53/08 ,  F02B2053/005 ,  F05D2220/40 ,  F05D2260/961 ,  Y02T10/144

Abstract: An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is configured to receive at least part of the pulsed flow. The first and second outlet nozzles each define a respective nozzle area communicating between the internal volume and a flow path of the turbine. The first and second outlet nozzles are spaced from one another with the first outlet nozzle located closer to the inlet port than the second outlet nozzle relative to a flow direction through the duct, the nozzle area of the first outlet nozzle being smaller than the nozzle area of the second outlet nozzle. A compound engine assembly and method of introducing a pulsed flow into a flow path of a turbine are also discussed.

公开(公告)号：US20170051666A1

公开(公告)日：2017-02-23

申请号：US15346864

申请日：2016-11-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN

IPC: F02B53/14 ,  F01C11/00 ,  F02B53/10

CPC classification number: F02B53/14 ,  F01C1/22 ,  F01C11/002 ,  F01C11/008 ,  F02B53/10 ,  F02B2053/005 ,  F02C6/12 ,  F02C6/20

Abstract: A compound cycle engine having a rotary internal combustion engine, a first turbine, and a second turbine is discussed. The exhaust port of the internal combustion engine is in fluid communication with the flowpath of the first turbine upstream of its rotor. The rotors of the first turbine and of each rotary unit drive a common load. The inlet of the second turbine is in fluid communication with the flowpath of the first turbine downstream of its rotor. The first turbine is configured as a velocity turbine and the first turbine has a pressure ratio smaller than that of the second turbine. A method of compounding a rotary engine is also discussed.

Abstract translation: 讨论了具有旋转内燃机，第一涡轮机和第二涡轮机的复合循环发动机。 内燃机的排气口与其转子上游的第一涡轮机的流路流体连通。 第一涡轮机和每个旋转单元的转子驱动公共负载。 第二涡轮机的入口与其转子下游的第一涡轮机的流动路径流体连通。 第一涡轮被构造为速度涡轮机，并且第一涡轮机的压力比小于第二涡轮机的压力比。 还讨论了一种混合旋转发动机的方法。

公开(公告)号：US20170037774A1

公开(公告)日：2017-02-09

申请号：US15227318

申请日：2016-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony JONES ,  Andre JULIEN ,  David MENHEERE ,  Jean THOMASSIN ,  Richard ULLYOTT ,  Daniel VAN DEN HENDE

IPC: F02B53/14 ,  F02B63/04 ,  F02B53/04

CPC classification number: F02B53/14 ,  B64D41/00 ,  F02B53/04 ,  F02B63/04 ,  Y02T50/53

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.

Abstract translation: 用于飞行器的辅助动力单元包括旋转间歇内燃机，具有与发动机的出口流体连通的入口的涡轮机，与发动机混合的涡轮，具有与所述发动机的环境流体连通的入口的压缩机 飞机和与飞机流体连通的出口，压缩机可独立于涡轮机旋转，驱动地接合到压缩机的电动机和驱动地接合到发动机的转移发电机，转移发电机和电动机电连接以允许 电力传输。 压缩机或额外的压缩机可以与发动机的入口流体连通。 还讨论了一种操作飞行器的辅助动力单元的方法。

公开(公告)号：US20170037756A1

公开(公告)日：2017-02-09

申请号：US15227506

申请日：2016-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Serge DUSSAULT

IPC: F01N3/05 ,  F02B61/04 ,  B64D33/04 ,  F02B53/14 ,  F01N13/08 ,  B64D27/10

CPC classification number: F01N3/055 ,  B64D27/02 ,  B64D27/08 ,  B64D27/10 ,  B64D33/04 ,  B64D33/10 ,  F01N13/082 ,  F01N2260/022 ,  F01N2270/02 ,  F02B53/14 ,  F02B61/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C6/206 ,  F02C7/18 ,  F02K1/386 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.

Abstract translation: 一种用于飞行器的涡轮螺旋桨发动机组件，包括具有液体冷却剂系统的内燃机，与飞行器的环境流体连通的空气管道;容纳在空气管道内的热交换器，其具有与液体冷却剂流体连通的冷却剂通道 系统和空气通道与空气管道流体连通的空气通道，以及与内燃机的排气流体连通的排气管道。 排气管道具有位于热交换器下游的空气管道中的出口和空气管道的出口的上游，排气管道的出口与空气管道的周壁隔开。 在使用中，冷却空气流围绕废气流。 还讨论了在具有内燃机的涡轮螺旋桨发动机组件中排出空气和废气的方法。

公开(公告)号：US20160298530A1

公开(公告)日：2016-10-13

申请号：US15188378

申请日：2016-06-21

Applicant: Pratt & Whitney Canada Corp.

Inventor： Edwin SCHULZ ,  Jean THOMASSIN

IPC: F02B19/10 ,  F02M55/02 ,  F02B53/10

CPC classification number: F02B19/108 ,  F01C1/22 ,  F02B53/10 ,  F02M55/025 ,  Y02T10/125 ,  Y02T10/17

Abstract: An internal combustion engine with at least two movable bodies each being sealingly and movably received within a respective internal cavity to define at least one combustion chamber of variable volume. A pilot fuel injector and a main fuel injector are provided for each movable body. A first chamber of a common rail is in fluid communication with each main fuel injector, and a second chamber of the common rail in fluid communication with each pilot fuel injector. A first metering or pressure regulating valve is in fluid communication with the first chamber. A second metering or pressure regulating valve provides selective fluid communication between the first and second chambers; the metering or pressure regulating valves are settable at different pressure values from one another. The movable bodies may be reciprocating pistons. A method of combusting fuel in an internal combustion engine is also provided.

Abstract translation: 具有至少两个可移动体的内燃机各自密封地且可移动地容纳在相应的内腔内，以限定至少一个具有可变体积的燃烧室。 为每个可移动体设置了先导燃料喷射器和主燃料喷射器。 共轨的第一室与每个主燃料喷射器流体连通，并且共轨的第二室与每个引燃燃料喷射器流体连通。 第一计量或压力调节阀与第一腔室流体连通。 第二计量或压力调节阀在第一和第二腔室之间提供选择性的流体连通; 计量或压力调节阀可以彼此设定在不同的压力值。 可移动体可以是往复活塞。 还提供了一种在内燃机中燃烧燃料的方法。

公开(公告)号：US20160245171A1

公开(公告)日：2016-08-25

申请号：US15047362

申请日：2016-02-18

Applicant: Pratt & Whitney Canada Corp.

Inventor： Sylvain LAMARRE ,  Mike FONTAINE ,  Andre JULIEN ,  Michael GAUL ,  Jean THOMASSIN ,  Lazar MITROVIC ,  Ilya B. MEDVEDEV ,  Sergey USIKOV ,  Andrey ZOLOTOV

IPC: F02C3/10 ,  F02B39/04 ,  F02B37/00

CPC classification number: F02C3/10 ,  F02B37/004 ,  F02B39/04 ,  F02C7/20 ,  F02C7/25 ,  F05D2220/40 ,  Y02T50/53

Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, compressor and engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and exhaust pipe(s). The struts are separated from the hot zone by at least one firewall. The mount cage may include a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and exhaust pipe(s) being located outside of the axial space.

Abstract translation: 具有包括至少一个内燃机，涡轮部分和具有与发动机芯的入口流体连通的出口的压缩机的发动机芯的复合发动机组件。 壳体连接到涡轮部分，压缩机和发动机核心。 安装架连接到在压缩机和包括涡轮部分和排气管的热区之间附接到壳体的安装件。 支柱通过至少一个防火墙与热区隔开。 安装架可以包括多个支柱，其全部从支架延伸离开涡轮部分和发动机芯。 壳体可以是齿轮箱模块壳体，涡轮轴通过该外壳与发动机轴接合。 安装架可以完全容纳在轴向空间内，涡轮部分和排气管位于轴向空间的外部。

公开(公告)号：US20160245163A1

公开(公告)日：2016-08-25

申请号：US14864084

申请日：2015-09-24

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain LAMARRE ,  Mike FONTAINE ,  Andre JULIEN ,  Michael GAUL ,  Jean THOMASSIN ,  Lazar MITROVIC

IPC: F02B41/10 ,  F02B53/10 ,  F02B53/02

CPC classification number: F02B41/10 ,  F01C1/22 ,  F01C11/008 ,  F01C13/04 ,  F01C21/008 ,  F01D25/16 ,  F02B53/02 ,  F02B53/10 ,  F02B2053/005 ,  F02C6/12 ,  F02C6/206 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/40 ,  F05D2230/51 ,  F05D2230/72 ,  F05D2240/50 ,  F05D2260/4031 ,  F05D2300/121 ,  F05D2300/171

Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed.

Abstract translation: 一种复合发动机组件，其具有包括至少一个内燃机，压缩机和涡轮部分的发动机芯，其中涡轮轴被配置成与发动机轴组合动力。 涡轮机部分可以包括第一级涡轮机和第二级涡轮机。 涡轮轴由多个位于压缩机转子的同一侧的轴承旋转地支撑，并且全部位于涡轮转子的同一侧，例如全部位于压缩机转子之间， 和涡轮转子，使得压缩机转子和涡轮转子是悬臂式的。 还讨论了驱动飞行器的可旋转载荷的方法。

公开(公告)号：US20160061053A1

公开(公告)日：2016-03-03

申请号：US14471130

申请日：2014-08-28

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN

IPC: F01D17/06 ,  F02C3/10

CPC classification number: F01D17/06 ,  F02C3/10 ,  F02C6/14 ,  F02C7/32 ,  F05D2220/50

Abstract: Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system.

Abstract translation: 描述了在瞬态条件下操作这种飞机发动机的飞机发动机和方法。 一种示例性方法包括识别飞机发动机的瞬态状态，并使用飞行器的电气系统至少部分地吸收瞬态状态。 当瞬态条件需要加速发动机时，吸收瞬态条件可包括将动力从电系统传递到发动机的高压阀芯。 当瞬态条件需要发动机减速时，吸收瞬态条件可包括将动力从高压阀芯传递到电气系统。

公开(公告)号：US20160047299A1

公开(公告)日：2016-02-18

申请号：US14926357

申请日：2015-10-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN

IPC: F02B53/10 ,  F02D41/38

CPC classification number: F02B53/10 ,  F01C1/22 ,  F02B19/108 ,  F02B55/14 ,  F02B2275/32 ,  F02D41/3094 ,  F02D41/3827 ,  F02D41/3836 ,  Y02T10/125 ,  Y02T10/142 ,  Y02T10/17

Abstract: An internal combustion engine including a pilot subchamber, a pilot fuel injector having a tip in communication with the pilot subchamber, an ignition element positioned to ignite fuel within the pilot subchamber, and a main fuel injector spaced apart from the pilot fuel injector. The engine includes a common rail in fluid communication with the main fuel injector and with the pilot fuel injector. The internal combustion engine may be a reciprocating engine. A method of combusting fuel in an internal combustion engine is also provided.

Abstract translation: 一种内燃机，包括导向子室，具有与导向子室连通的尖端的先导燃料喷射器，定位成点燃先导子室内的燃料的点火元件和与先导燃料喷射器间隔开的主燃料喷射器。 发动机包括与主燃料喷射器和引燃燃料喷射器流体连通的共轨。 内燃机可以是往复式发动机。 还提供了一种在内燃机中燃烧燃料的方法。