公开(公告)号：US20160245166A1

公开(公告)日：2016-08-25

申请号：US14806880

申请日：2015-07-23

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN ,  Sebastien BOLDUC ,  Bruno VILLENEUVE ,  Stephane BERUBE ,  Mike FONTAINE ,  David GAGNON-MARTIN ,  Jade BILODEAU ,  Andre JULIEN ,  Pierre-Yves LEGARE ,  Jason NICHOLS

IPC: F02B53/14 ,  F02C3/04

CPC classification number: F02B53/14 ,  F01C1/22 ,  F01C11/008 ,  F01C21/18 ,  F02B29/0418 ,  F02B33/40 ,  F02B39/04 ,  F02B41/10 ,  F02B2053/005 ,  F02C3/04 ,  F02C3/107 ,  F02C6/00 ,  F02C6/12 ,  F02C6/20 ,  F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/14 ,  F02C7/36 ,  F02M31/042 ,  F02M31/10 ,  F02M31/107 ,  F05D2250/312 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T10/126 ,  Y02T10/146 ,  Y02T10/163 ,  Y02T10/17 ,  Y02T50/675

Abstract: A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

Abstract translation: 一种复合发动机组件，其具有包括与发动机轴驱动接合的至少一个内燃机的发动机机芯，具有与发动机机芯的入口流体连通的出口的压缩机，并且包括至少一个转子， 发动机轴，与压缩机转子驱动接合的发动机轴，以及涡轮部，其具有与发动机芯的出口流体连通的入口，并且包括接合在可旋转的涡轮轴上的至少一个转子，所述涡轮轴被配置为 与发动机轴组合动力。 涡轮机和发动机轴彼此平行并径向偏移，并且涡轮轴和压缩机转子的轴线彼此平行并径向偏移。 还讨论了驱动飞行器的可旋转载荷的方法。

公开(公告)号：US20160245162A1

公开(公告)日：2016-08-25

申请号：US14864096

申请日：2015-09-24

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: F02B41/00 ,  F01C11/00 ,  F02C7/36 ,  F01C21/18 ,  F01C1/22

CPC classification number: F02B41/00 ,  F01C1/22 ,  F01C11/008 ,  F01C21/18 ,  F02C6/12 ,  F02C6/206 ,  F02C7/052 ,  F02C7/36 ,  F05B2220/40 ,  F05D2220/323 ,  F05D2230/51 ,  F05D2230/72 ,  F05D2250/312 ,  F05D2260/4031 ,  F05D2300/121 ,  F05D2300/171

Abstract: A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft 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 and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

Abstract translation: 具有入口管道，压缩机，包括至少一个内燃机的发动机核心的复合发动机组件和包括被配置为与发动机轴组合动力的涡轮轴的涡轮部分。 涡轮机部分可以包括第一级涡轮机和第二级涡轮机。 涡轮轴和发动机轴彼此平行。 涡轮机轴，发动机轴和入口管道的至少一部分都相互径向偏移。 还讨论了驱动飞行器的可旋转载荷的方法。

公开(公告)号：US20140261293A1

公开(公告)日：2014-09-18

申请号：US13796216

申请日：2013-03-12

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Edwin SCHULZ ,  Jean THOMASSIN

IPC: 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 rotatable bodies each defining at least one combustion chamber of variable volume and, for each rotatable body: 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 first fuel conduit in fluid communication with each main fuel injector, and a common second fuel conduit in fluid communication with each pilot fuel injector. First and second pressure regulating mechanisms which are settable at different pressure values from one another respectively regulate a fuel pressure in the first and second conduits. A method of combusting fuel in an internal combustion engine is also provided.

Abstract translation: 一种具有至少两个可旋转体的内燃机，每个至少两个旋转体限定至少一个具有可变体积的燃烧室，并且对于每个可旋转体，导引子室，具有与导向子室连通的尖端的引燃燃料喷射器，点火元件， 在飞行员子舱内点燃燃料，以及与引燃燃料喷射器间隔开的主燃料喷射器。 发动机包括与每个主燃料喷射器流体连通的公共第一燃料管道，以及与每个引燃燃料喷射器流体连通的公共第二燃料管道。 可在彼此不同压力值下设定的第一和第二压力调节机构分别调节第一和第二管道中的燃料压力。 还提供了一种在内燃机中燃烧燃料的方法。

公开(公告)号：US20200217248A1

公开(公告)日：2020-07-09

申请号：US16822396

申请日：2020-03-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Serge DUSSAULT

IPC: F02C5/06 ,  F02C9/18 ,  F02K3/06 ,  F02C7/36 ,  F02B53/02 ,  F02C7/18 ,  F02C5/00 ,  F02C7/143 ,  F02K5/00

Abstract: A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

公开(公告)号：US20190256214A1

公开(公告)日：2019-08-22

申请号：US15898741

申请日：2018-02-19

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Luc DIONNE ,  Bruno VILLENEUVE ,  Jean THOMASSIN

IPC: B64D27/08 ,  F02B53/14 ,  F02B41/10 ,  B64C25/16 ,  B64C25/14 ,  B64C25/34 ,  B64D29/04 ,  B64D33/08 ,  B64D35/02

Abstract: An assembly for an aircraft having a propeller, including a wheel well configured for receiving a retracted landing gear, the wheel well including walls and a closable bottom opening for deploying the landing gear therethrough, an engine assembly having an engine shaft configured for driving engagement with the propeller, and a mount assembly for supporting the engine assembly, the mount assembly connected to at least one of the walls of the wheel well. A method of supporting an engine assembly in an aircraft having a retractable landing gear and a propeller driven by the engine assembly is also discussed.

公开(公告)号：US20190112973A1

公开(公告)日：2019-04-18

申请号：US16164148

申请日：2018-10-18

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: F02B41/00 ,  F02C6/20 ,  F02C7/052 ,  F02C7/36 ,  F01C21/18 ,  F01C11/00 ,  F02C6/12

Abstract: A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft 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 and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

公开(公告)号：US20190107042A1

公开(公告)日：2019-04-11

申请号：US16177752

申请日：2018-11-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Andre JULIEN ,  Serge DUSSAULT

IPC: F02B19/10

Abstract: A method of combusting fuel, e.g. heavy fuel, in a rotary engine, including injecting a main quantity of fuel directly into a combustion chamber to form a first fuel-air mixture having a first air-fuel equivalence ratio λ higher than 1, injecting a pilot quantity of fuel into a pilot subchamber to form a second fuel-air mixture having a second air-fuel equivalence ratio λ smaller than the first air-fuel equivalence ratio, igniting the second fuel-air mixture within the pilot subchamber, using the ignited second fuel-air mixture from the pilot subchamber to ignite the first fuel-air mixture, and injecting a supplemental quantity of fuel directly into the combustion chamber after igniting the first fuel-air mixture, upstream of an exhaust port of the rotary engine with respect to a direction of rotation of the rotor. A rotary engine with interburner fuel injector is also discussed.

公开(公告)号：US20190085774A1

公开(公告)日：2019-03-21

申请号：US15708919

申请日：2017-09-19

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Bruno VILLENEUVE ,  Mike FONTAINE

IPC: F02D23/00 ,  F02B53/14 ,  F02B37/00 ,  B64D27/04 ,  B64D41/00

CPC classification number: F02D23/00 ,  B64D27/04 ,  B64D41/00 ,  F02B37/004 ,  F02B37/105 ,  F02B41/10 ,  F02B53/02 ,  F02B53/14 ,  F02B2053/005 ,  F02C3/00 ,  F02C3/055 ,  F02C3/107 ,  F02C6/00 ,  F02C6/12 ,  F02C7/26 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/40 ,  F16D11/14 ,  F16D48/06 ,  F16D2500/10418 ,  F16D2500/10462

Abstract: A method of operating a compoundable engine that includes a turbine having a turbine shaft and an intermittent internal combustion engine having an engine shaft. The engine shaft is rotated at a first rotational speed. The turbine is driven by exhaust gases of the intermittent internal combustion engine to rotate the turbine shaft while the engine shaft rotates independently from the turbine shaft. A rotatable load is driven with the turbine shaft. A rotational speed of the engine shaft is increased from the first rotational speed until the turbine shaft reaches a predetermined rotational speed. After the turbine shaft has reached the predetermined rotational speed, the rotational speed of the engine shaft is adjusted until the turbine shaft and the engine shaft are drivingly engageable with each other, and the turbine shaft with the engine shaft are engaged such that both are in driving engagement with the rotatable load.

公开(公告)号：US20190055882A1

公开(公告)日：2019-02-21

申请号：US16168045

申请日：2018-10-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Nigel DAVENPORT ,  Eugene GEKHT

IPC: F02B55/08 ,  F02B19/12 ,  F02B53/02 ,  F02B53/10 ,  F02B53/12 ,  F01C21/18 ,  F01C1/22 ,  F01C21/10 ,  F01C21/06 ,  F01C11/00 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/08 ,  F04C29/00

Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.

公开(公告)号：US20180030883A1

公开(公告)日：2018-02-01

申请号：US15708442

申请日：2017-09-19

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Sebastien BOLDUC ,  Bruno VILLENEUVE ,  Stephane BERUBE ,  Mike FONTAINE ,  David GAGNON-MARTIN ,  Andre JULIEN ,  Mark CUNNINGHAM ,  Serge LAFORTUNE ,  Pierre-Yves LEGARE

IPC: F02B29/04 ,  F01C11/00 ,  F01D13/00 ,  F02B33/34 ,  F02C6/12 ,  F02B61/04 ,  F01C1/22 ,  F02B41/10 ,  F02B53/00 ,  F02K5/00

CPC classification number: F02B29/0493 ,  B64D33/02 ,  B64D2033/0293 ,  F01C1/22 ,  F01C11/002 ,  F01C11/008 ,  F01D13/003 ,  F02B29/0412 ,  F02B29/0418 ,  F02B33/34 ,  F02B41/10 ,  F02B53/00 ,  F02B61/04 ,  F02B2053/005 ,  F02C6/12 ,  F02K5/00 ,  F05D2220/40 ,  Y02T10/146 ,  Y02T10/163 ,  Y02T10/17

Abstract: A compound engine assembly including a common air conduit having an inlet in fluid communication with ambient air, a compressor, at least one internal combustion engine having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the at least one internal combustion engine, the turbine section configured to compound power with the at least one internal combustion engine, and at least one heat exchanger in fluid communication with the common air conduit, each of the at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the common air conduit circulating therethrough. The compressor has an inlet in fluid communication with the common air conduit upstream of the at least one heat exchanger. The internal combustion engine may be a reciprocating engine.