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：US20180118369A1

公开(公告)日：2018-05-03

申请号：US15797249

申请日：2017-10-30

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Lazar MITROVIC ,  Richard ULLYOTT

IPC: B64D41/00 ,  B64D15/14 ,  F16H3/66 ,  B64C11/02 ,  B64C11/44 ,  B64D15/12 ,  B64D27/10 ,  F02C7/32

Abstract: Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.

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：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：US20190323436A1

公开(公告)日：2019-10-24

申请号：US15958437

申请日：2018-04-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Lazar MITROVIC

IPC: F02C7/36 ,  F01D15/12 ,  F02C3/04

Abstract: A gear assembly for a gas turbine engine has an input gear adapted to be secured to a turbine shaft. An output gear is adapted to be secured to a compressor shaft, the input gear and the output gear having the same number of teeth. A pair of idler gear shafts is provided, each said idler gear shaft having a first stage gear meshed with the input gear to be driven by the turbine shaft at a first stage of speed change. A second stage gear is axially spaced from the first stage gear and rotates with the first stage gear. The second stage gear is meshed with the output gear to drive the compressor shaft at a second stage of speed change. Landmarks are provided for aligning the gears during assembly in a desired orientation.

公开(公告)号：US20190017442A1

公开(公告)日：2019-01-17

申请号：US15651289

申请日：2017-07-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Ian MACFARLANE ,  Lazar MITROVIC

IPC: F02C7/32 ,  F02C3/04 ,  F02C7/04 ,  F02C7/06

CPC classification number: F02C7/32 ,  F01D9/045 ,  F01D9/065 ,  F01D15/12 ,  F02C3/04 ,  F02C7/04 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/60 ,  F05D2260/40

Abstract: A radial air inlet for a gas turbine engine. The air inlet has an inlet duct defined between two axially-spaced radially-extending annular walls and has a plurality of circumferentially-spaced axially-extending struts extending between the annular walls adjacent a radially-outer portion of the air inlet. At least one of the struts has an internal passage extending between a first opening in a forward end of the strut and a second opening in an aft end of the strut, the first and second openings being axially spaced apart. A transmission shaft extends through the internal passage of said strut.

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.

公开(公告)号：US20180135522A1

公开(公告)日：2018-05-17

申请号：US15351803

申请日：2016-11-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Lazar MITROVIC ,  Jean DUBREUIL ,  Eric DUROCHER ,  Keith MORGAN ,  Michel DESJARDINS

IPC: F02C7/36 ,  F02C3/04 ,  F02C7/04

Abstract: A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.