公开(公告)号：US20170327241A1

公开(公告)日：2017-11-16

申请号：US15412451

申请日：2017-01-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Lazar MITROVIC ,  Eric DUROCHER ,  Keith MORGAN

IPC: B64D35/08 ,  F02C7/262 ,  B64D27/10 ,  B64D31/06 ,  F02C7/275 ,  B64C27/12 ,  F02C7/22 ,  F02C6/02 ,  F16D48/02 ,  F02C7/36

Abstract: A method of operating a twin engine helicopter power plant, the power plant comprising: two turboshaft engines each having an engine shaft with a turbine at a distal end and a one-way clutch at a proximal end; a gear box having an input driven by the one way clutch of each engine and an output driving a helicopter rotor; a bypass clutch disposed between the proximal end of each engine shaft and the input of the gear box; and power plant management system controls for activating the bypass clutch; the method comprising: detecting when a rotary speed of an associated engine shaft is less than a rotary speed of the gear box input; activating the bypass clutch to drive the associated engine shaft using the rotation of the gear box input; and starting an associated engine by injecting fuel when the bypass clutch is activated.

公开(公告)号：US20160281609A1

公开(公告)日：2016-09-29

申请号：US14670551

申请日：2015-03-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Lazar MITROVIC ,  Keith MORGAN ,  Danny MILLS

IPC: F02C7/36 ,  F02C7/32 ,  F16H37/04

CPC classification number: F02C7/36 ,  F02C3/10 ,  F02C3/107 ,  F02C6/206 ,  F02C7/32 ,  F02K3/025 ,  F05D2220/325 ,  F05D2220/326 ,  F05D2250/313 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H1/22 ,  F16H1/222 ,  F16H37/041 ,  Y02T50/671

Abstract: The described reduction gearbox of a gas turbine engine includes a first gear reduction stage having an input gear adapted to be driven by a turbine output shaft. The input gear transfers power received from the turbine output shaft laterally away from the input gear to an input speed gear. Each input speed gear engages an output speed gear to define a main speed reduction gear set, and the main speed reduction gear sets are laterally spaced apart from one another to define a gap. The gearbox has a second gear reduction stage driven by the output speed gears, the second stage adapted to drive an engine output shaft.

Abstract translation: 所描述的燃气涡轮发动机的减速齿轮箱包括具有适于由涡轮机输出轴驱动的输入齿轮的第一齿轮减速级。 输入齿轮将从涡轮机输出轴接收的功率从输入齿轮横向移动到输入速度齿轮。 每个输入速度齿轮接合输出速度齿轮以限定主减速齿轮组，并且主减速齿轮组彼此横向间隔开以限定间隙。 齿轮箱具有由输出转速齿轮驱动的第二档位减速级，第二级适于驱动发动机输出轴。

公开(公告)号：US20150322864A1

公开(公告)日：2015-11-12

申请号：US14802569

申请日：2015-07-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Kevin Allan DOOLEY ,  Keith MORGAN

IPC: F02C7/266

CPC classification number: F02C7/26 ,  B64C27/12 ,  B64D35/08 ,  F01D15/10 ,  F02C7/266 ,  F02C7/268 ,  F02N11/006 ,  F02N11/04 ,  F02N11/0844 ,  F02N11/0866 ,  F02N2011/0885 ,  F05D2220/329 ,  F05D2220/74 ,  F05D2240/40 ,  F05D2260/42 ,  F05D2260/85 ,  Y02T50/671

Abstract: A multi-engine system 10 for use on an aircraft 14 is disclosed. The system 10 may comprise a first aircraft engine 16A and a second aircraft engine 16B configured to drive at least one device 12 of the aircraft 14. A starter 20 may be coupled to one of the first and second aircraft engines 16A, 16B to assist starting of the one of the first and second aircraft engines 16A, 16B. An energy source 24 may be configured to deliver energy to the starter 20 at a rapid rate during rapid starting of the one of the first and the second aircraft engines 16A, 16B, the rapid rate being higher than a regular rate used during regular starting of the one of the first and the second aircraft engines 16A, 16B. The energy source 24 may comprise at least one supercapacitor.

Abstract translation: 公开了一种在飞机14上使用的多发动机系统10。 系统10可以包括第一飞行器引擎16A和被配置为驱动飞机14的至少一个设备12的第二飞行器引擎16B。起动器20可以联接到第一和第二飞行器引擎16A，16B中的一个以辅助启动 的第一和第二飞行器引擎16A，16B中的一个。 能量源24可以被配置为在第一和第二飞行器引擎16A，16B中的一个飞行器引擎16A，16B的快速启动期间以快速的速率向启动器20输送能量，快速率高于在正常启动期间使用的常规速率 第一和第二飞机发动机16A，16B中的一个。 能量源24可以包括至少一个超级电容器。

公开(公告)号：US20210047964A1

公开(公告)日：2021-02-18

申请号：US16991224

申请日：2020-08-12

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Laurent LETOURNEAU ,  Keith MORGAN ,  John WILSON ,  Paul WEAVER ,  Eric DUROCHER

IPC: F02C7/052 ,  F02C7/04 ,  F02C7/14 ,  B64D27/12 ,  B64D33/02 ,  B64D33/08

Abstract: A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC).

公开(公告)号：US20200095942A1

公开(公告)日：2020-03-26

申请号：US16583896

申请日：2019-09-26

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric DUROCHER ,  Keith MORGAN ,  Lazar MITROVIC ,  Jean DUBREUIL ,  Martin POULIN

IPC: F02C7/32 ,  F02C6/20 ,  F02C3/10 ,  F02C3/14

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

公开(公告)号：US20180073428A1

公开(公告)日：2018-03-15

申请号：US15266321

申请日：2016-09-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Keith MORGAN ,  Robert PELUSO ,  Ghislain PLANTE ,  Eugene GEKHT ,  Eric DUROCHER ,  Jean DUBREUIL

IPC: F02C3/10 ,  F02C3/09 ,  F02C7/32 ,  F02C7/36 ,  F02K3/04

CPC classification number: F02C7/32 ,  F02C3/145 ,  F02C6/206 ,  Y02T50/671

Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

公开(公告)号：US20170037785A1

公开(公告)日：2017-02-09

申请号：US15332045

申请日：2016-10-24

Applicant: Pratt & Whitney Canada Corp.

Inventor： Keith MORGAN ,  Francois BELLEVILLE

IPC: F02C9/20 ,  F02C9/26

CPC classification number: F02C9/20 ,  F02C3/10 ,  F02C9/00 ,  F02C9/26 ,  F05D2270/023

Abstract: A method of controlling a speed of a gas turbine engine, the gas turbine engine including a high pressure spool and a low pressure spool rotating independently from one another, including determining a temperature-corrected rotational speed of the high pressure spool based on an actual rotational speed of the high pressure spool and on an air temperature measured outside of the gas turbine engine; controlling the rotation of the high pressure spool to maintain the temperature-corrected rotational speed of the high pressure spool at least substantially constant throughout a range of a power demand on the gas turbine engine; and controlling a rotational speed of the low pressure spool independently of the rotation of the high pressure spool.

Abstract translation: 一种控制燃气涡轮发动机的速度的方法，所述燃气涡轮发动机包括彼此独立地相互旋转的高压阀芯和低压阀芯，包括基于实际转速确定高压阀芯的温度校正转速 高压阀芯的速度和在燃气涡轮发动机外部测量的空气温度; 控制高压阀芯的旋转以在燃气涡轮发动机的功率需求的范围内保持高压阀芯的温度校正转速至少基本上恒定; 并且独立于高压阀芯的旋转来控制低压阀芯的转速。

公开(公告)号：US20140290265A1

公开(公告)日：2014-10-02

申请号：US13754304

申请日：2013-01-30

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard ULLYOTT ,  Keith MORGAN ,  Jean DUBREUIL ,  Lazar MITROVIC ,  Kevin A. DOOLEY ,  Stephen KENNY ,  Ilya MEDVEDEV ,  Johnny VINSKI

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F02C3/113 ,  F05D2220/324 ,  F05D2220/327

Abstract: A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.

Abstract translation: 具有差速器的多线轴燃气涡轮发动机具有可选择性地旋转的构件，其转速确定差速器的驱动和驱动构件的转速之间的可变比。 被驱动构件接合到第一卷轴，并且与其它卷轴（例如，连接到压缩机转子）无关的可旋转轴接合到驱动构件。 第一和第二动力传递装置分别接合到第一卷轴和可选择性旋转的构件。 电路将功率传输装置互连并允许它们之间的电力传输，并且控制单元控制在功率传输装置之间传输的功率。 因此能够在第一卷轴和可选择性地旋转的构件之间传递动力，以改变第一卷轴和可旋转轴之间的速比。

公开(公告)号：US20210270183A1

公开(公告)日：2021-09-02

申请号：US17077310

申请日：2020-10-22

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Keith MORGAN ,  Robert PELUSO ,  Ghislain PLANTE ,  Eugene GEKHT ,  Eric DUROCHER ,  Jean DUBREUIL ,  Stephen MAH ,  Philippe BEAUCHESNE-MARTEL

IPC: F02C3/067 ,  F02C3/04 ,  F02C3/113 ,  F02C7/36 ,  F01D1/26 ,  F04D25/02

Abstract: A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.

公开(公告)号：US20180283468A1

公开(公告)日：2018-10-04

申请号：US15484506

申请日：2017-04-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Lazar MITROVIC ,  Keith MORGAN

IPC: F16D25/061 ,  F16D25/12 ,  F16D11/14 ,  F02C7/36 ,  B64D27/10

Abstract: A clutch device for a gas turbine engine having a sliding coupling mounted to the engine and slidingly displaceable therein. The sliding coupling is mountable between the gearbox and the output shaft. The sliding coupling is continuously engageable with the gearbox and is selectively engageable with the output shaft to mechanically couple the output shaft to the gearbox. The sliding coupling is slidingly displaceable between a first position in which the sliding coupling is mechanically coupled to the output shaft to transmit a rotational drive of the output shaft to the gearbox, and a second position in which the sliding coupling is disengaged from the output shaft. A piston is disposed within the engine and acts on the sliding coupling to displace the sliding coupling to at least the second position.