公开(公告)号：US20160376981A1

公开(公告)日：2016-12-29

申请号：US14750157

申请日：2015-06-25

Applicant: Pratt & Whitney Canada Corp.

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

IPC: F02B63/04 ,  F01C11/00 ,  F02C7/36 ,  F02B53/02 ,  F02B37/013

Abstract: A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract translation: 一种用作飞行器的辅助动力单元并且包括具有内燃机的发动机芯的复合发动机组件，具有与发动机芯入口流体连通的出口的压缩机，与压缩机流体连通的排放管道 出口通过放气阀，以及涡轮部分，其具有与发动机芯出口流体连通的入口并且被配置成与发动机芯组合功率。 涡轮机部分可以包括具有与发动机芯出口流体连通的入口的第一级涡轮机和具有与第一级涡轮机出口流体连通的入口的第二级涡轮机。 还讨论了向飞行器提供压缩空气和电力的方法。

公开(公告)号：US20160245185A1

公开(公告)日：2016-08-25

申请号：US14864112

申请日：2015-09-24

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: F02C7/36 ,  F02C3/04 ,  F23M11/02

CPC classification number: F02C7/36 ,  F01C1/22 ,  F01C11/008 ,  F02C3/04 ,  F02C6/12 ,  F02C7/25 ,  F05D2220/323 ,  F05D2230/51 ,  F05D2230/72 ,  F05D2250/312 ,  F05D2260/4031 ,  F05D2300/121 ,  F05D2300/171 ,  F23M11/02

Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section including a turbine shaft in driving engagement with the engine shaft, and a compressor, and a firewall. The compressor is located on one side of the firewall, and the turbine section and the engine core are located on the other side. The assembly may include a gearbox module with the turbine section and the engine core located on a same side of the gearbox module casing and the compressor located on the opposite side of the gearbox module casing, and with the firewall extending from the gearbox module casing. One or more rotatable accessory may be located on a same side of the firewall as the compressor. A method of reducing fire hazard in a compound engine assembly is also discussed.

Abstract translation: 具有包括至少一个内燃机的发动机芯的复合发动机组件，包括与发动机轴驱动接合的涡轮轴的涡轮部分，以及压缩机和防火墙。 压缩机位于防火墙的一侧，涡轮部分和发动机核心位于另一侧。 组件可以包括齿轮箱模块，其中涡轮部分和发动机芯位于齿轮箱模块壳体的同一侧并且压缩机位于齿轮箱模块壳体的相对侧上，防火墙从齿轮箱模块壳体延伸。 一个或多个可旋转附件可以位于防火墙与压缩机相同的一侧。 还讨论了在复合发动机组件中减少火灾危险的方法。

公开(公告)号：US20160245161A1

公开(公告)日：2016-08-25

申请号：US14806902

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 ,  Andre JULIEN ,  Mark CUNNINGHAM ,  Serge LAFORTUNE ,  Pierre-Yves LEGARE

IPC: F02B41/00 ,  F01C1/22 ,  F02C6/18 ,  F01C11/00 ,  F02C3/04 ,  F01C21/18 ,  F01C21/06

CPC classification number: F02B41/00 ,  B64D33/10 ,  F01C1/22 ,  F01C11/008 ,  F01C21/06 ,  F01C21/18 ,  F02C3/04 ,  F02C6/18 ,  F02C7/04 ,  F02C7/042 ,  F02C7/14 ,  Y02T50/675

Abstract: A compound engine assembly including a compressor, an engine core including at least one rotary internal combustion engine and 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 engine core and configured to compound power with the engine core, and an air conduit having at least one heat exchanger extending thereacross. An outer wall of the air conduit has a plurality of openings defined therethrough downstream of the heat exchanger(s), each selectively closable by a pivotable flap movable between a retracted position where the opening is obstructed and an extended position away from the opening. Each opening defines a fluid communication between the air conduit and the ambient air when the respective flap is in the extended position. A method of directing flow through a compound engine assembly is also discussed.

Abstract translation: 一种复合发动机组件，包括压缩机，包括至少一个旋转内燃机的发动机内燃机，并且具有与压缩机的出口流体连通的入口，具有与发动机芯的出口流体连通的入口的涡轮部分，以及 配置成与发动机芯组合动力，以及具有至少一个在其上延伸的热交换器的空气管道。 空气管道的外壁具有在热交换器的下游限定的多个开口，每个开口可由可枢转的翼片选择性地关闭，所述枢转折翼可在开口被阻塞的缩回位置和远离开口的延伸位置之间移动。 当各个翼片处于伸出位置时，每个开口限定了空气管道和环境空气之间的流体连通。 还讨论了引导流过复合发动机组件的方法。

公开(公告)号：US20160245156A1

公开(公告)日：2016-08-25

申请号：US14864068

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: F02B37/10 ,  F02B53/14 ,  F02B53/02 ,  B64D27/02 ,  F02B33/40

CPC classification number: F02B37/105 ,  B64D27/02 ,  F01C1/22 ,  F01C11/008 ,  F02B33/40 ,  F02B53/02 ,  F02B53/14 ,  F02B2053/005 ,  F02C6/12 ,  F02C6/206 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/40 ,  F05D2230/51 ,  F05D2230/72 ,  F05D2250/312 ,  F05D2260/4031 ,  F05D2300/121 ,  F05D2300/171

Abstract: An engine assembly including an engine core with at least one internal combustion engine, a first casing, a turbine module including a second casing located outside of the first casing, and a compressor module including a third casing located outside of the first and second casings. The turbine shaft extends into the first casing, is rotationally supported by a bearings all contained within the first casing, and is free of rotational support within the second casing. The first casing may be a gearbox module casing through which the turbine shaft is in driving engagement with the engine shaft. A method of driving a rotatable load of an aircraft, and an engine assembly with a rotary engine core, a gearbox module with a first casing, and a second module including a second casing located outside of the first casing and detachably connected to the first casing are also discussed.

Abstract translation: 一种发动机组件，包括具有至少一个内燃机的发动机芯，第一壳体，包括位于第一壳体外部的第二壳体的涡轮机模块，以及包括位于第一和第二壳体外部的第三壳体的压缩机模块。 涡轮轴延伸到第一壳体中，由全部包含在第一壳体内的轴承旋转地支撑，并且在第二壳体内不具有旋转支撑。 第一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驱动接合。 一种驱动飞行器的可旋转载荷的方法，以及具有旋转发动机芯的发动机组件，具有第一壳体的齿轮箱模块和包括位于第一壳体外部的第二壳体的第二模块，并且可拆卸地连接到第一壳体 也被讨论。

公开(公告)号：US20160245152A1

公开(公告)日：2016-08-25

申请号：US14806883

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 ,  Andre JULIEN ,  Mark CUNNINGHAM ,  Serge LAFORTUNE ,  Pierre-Yves LEGARE

IPC: F02B29/04 ,  F02B53/08 ,  F02B53/14 ,  F02B37/12

CPC classification number: F02B29/0406 ,  F01C1/22 ,  F01C11/008 ,  F01C21/18 ,  F02B29/0412 ,  F02B33/40 ,  F02B37/12 ,  F02B39/04 ,  F02B53/08 ,  F02B53/14 ,  F02C6/12 ,  F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/14 ,  F02C7/36 ,  F02M31/042 ,  F02M31/10 ,  F02M31/107 ,  F05D2250/312 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T10/126 ,  Y02T10/17 ,  Y02T50/675

Abstract: An intake assembly for a compressor providing compressed air to an internal combustion engine core, including an air conduit having at least one heat exchanger extending thereacross, an intake plenum for the compressor, a first intake conduit connected to the air conduit upstream of the heat exchanger(s), a second intake conduit connected to the air conduit downstream of the heat exchanger(s), and a selector valve configurable between a first configuration to allow a fluid communication between the intake plenum and the air conduit through the first intake conduit and a second configuration to prevent the fluid communication through the first intake conduit. Fluid communication between the intake plenum and the air conduit through the second intake conduit is allowed at least when the selector valve is in the second configuration. An engine assembly and method of supplying air to a compressor are also discussed.

Abstract translation: 一种用于压缩机的进气组件，其向内燃机芯提供压缩空气，包括具有至少一个在其上延伸的热交换器的空气导管，用于压缩机的进气增压室，连接到热交换器上游的空气管道的第一进气管 连接到所述热交换器下游的所述空气导管的第二进气管，以及可配置在允许所述进气室和所述空气管通过所述第一进气管道之间的流体连通的第一配置之间的选择阀，以及 第二构造，用于防止通过第一进气管道的流体连通。 至少当选择阀处于第二配置时，容许通过第二进气管进气通道和空气管道之间的流体连通。 还讨论了一种向压缩机供应空气的发动机组件和方法。

公开(公告)号：US20150075483A1

公开(公告)日：2015-03-19

申请号：US14549783

申请日：2014-11-21

Applicant: Pratt & Whitney Canada Corp.

Inventor： Mike FONTAINE ,  Andre JULIEN ,  Jean THOMASSIN

IPC: F02B53/02 ,  F04C2/12 ,  F02B53/08 ,  F02B55/16 ,  F02B55/14

CPC classification number: F02B53/02 ,  F01C1/22 ,  F01C11/006 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/06 ,  F01C21/08 ,  F01C21/106 ,  F01C21/18 ,  F01C21/183 ,  F02B53/08 ,  F02B55/14 ,  F02B55/16 ,  F02B2053/005 ,  F04C2/12 ,  F04C29/0092 ,  F04C2240/80 ,  Y10S60/901

Abstract: In one aspect, described is a rotary engine having a purge port located rearwardly of the inlet port and forwardly of the exhaust port along a direction of the revolutions of the rotor, the purge port being in communication with the exhaust port through each of the chambers along a respective portion of each revolution, and the inlet and outlet ports being relatively located such that a volumetric compression ratio of the engine is lower than a volumetric expansion ratio of the engine.

Abstract translation: 在一个方面，描述了一种旋转发动机，其具有沿着转子的转动方向位于入口后方并且在排气口前方的排气口，净化口通过每个室与排气口连通 沿着每个旋转的相应部分，并且入口和出口相对定位成使得发动机的体积压缩比低于发动机的体积膨胀比。