公开(公告)号：US20140260295A1

公开(公告)日：2014-09-18

申请号：US13804799

申请日：2013-03-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard ULLYOTT ,  Lazar MITROVIC ,  Jean DUBREUIL ,  Stephen Christopher KENNY ,  Guy BOUCHARD ,  Ilya B. MEDVEDEV ,  Keith MORGAN ,  Daris Jehangir KARANJIA ,  Nashed Azer YOUSSEF

IPC: F02C3/113

CPC classification number: F02C3/113 ,  F02C3/107 ,  F02C7/36 ,  F02C9/56 ,  F05D2260/4031

Abstract: A method of adjusting a rotational speed of the low pressure compressor rotor(s) of a gas turbine engine, including rotating the high pressure compressor rotor(s) with the high pressure turbine rotor(s) through the high pressure spool, rotating the low pressure turbine rotor(s) with a flow of exhaust gases from the high pressure turbine, rotating the low pressure spool with the low pressure turbine rotor(s), rotating a load of the engine with the low pressure spool, driving a rotation of the low pressure compressor rotor(s) with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the compressor rotor(s) and the low pressure spool, and adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor(s). A method of adjusting rotational speeds of a gas turbine engine and a gas turbine engine are also described.

Abstract translation: 一种调节燃气涡轮发动机的低压压缩机转子的转速的方法，包括通过高压阀芯与高压涡轮转子一起旋转高压压缩机转子，使低压 来自高压涡轮机的废气流的高压涡轮机转子，用低压涡轮转子旋转低压阀芯，用低压阀芯旋转发动机的负载，驱动 通过限定压缩机转子和低压阀芯的转速之间的可变传动比的可变传动装置与低压阀芯连接的低压压缩机转子，并且调整传动比以获得所需的转速 低压压缩机转子。 还描述了一种调节燃气涡轮发动机和燃气涡轮发动机的转速的方法。

公开(公告)号：US20140241854A1

公开(公告)日：2014-08-28

申请号：US13775806

申请日：2013-02-25

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eugene GEKHT ,  Terrence LUCAS ,  Thomas Francis HASLAM-JONES ,  Danny MILLS ,  Guy BOUCHARD

IPC: F01D11/24

CPC classification number: F01D11/24 ,  F01D25/12 ,  F01D25/14 ,  F05D2220/321 ,  F05D2240/11 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2260/201 ,  Y02T50/676

Abstract: A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.

Abstract translation: 燃气涡轮发动机包括限定有外皮和穿孔内皮的环形增压室，用于接收选择性空气流以冲击支撑壳体，支撑壳体支撑发动机转子组件的护罩，用于转子组件的主动顶端间隙控制。 在一个实施例中，用于将冷却空气供应到通风室中的线轴式传送管设置在发动机的外壳和增压室之间，使得允许外壳和集气室的热诱导的相对运动。

公开(公告)号：US20210003458A1

公开(公告)日：2021-01-07

申请号：US16502341

申请日：2019-07-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric DUROCHER ,  Scott SMITH ,  Guy BOUCHARD

IPC: G01K7/02 ,  G01K13/02 ,  F02C9/18 ,  B01F3/02

Abstract: A system and method for measuring average temperature of gas in an axial cross-section of a gas turbine engine gas path, involving diverting gas samples from different positions in the axial cross-section to a gas mixing chamber and measuring a temperature of the resulting mixed gas.

公开(公告)号：US20180363913A1

公开(公告)日：2018-12-20

申请号：US15628257

申请日：2017-06-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy BOUCHARD ,  Kenneth PARKMAN

IPC: F23R3/48 ,  F23R3/50 ,  F23R3/26

CPC classification number: F23R3/48 ,  F01D1/023 ,  F01D11/02 ,  F01D25/125 ,  F01D25/183 ,  F01M2011/021 ,  F02C7/06 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/237 ,  F05D2260/941 ,  F16C33/1025 ,  F16C33/106 ,  F16C33/1085 ,  F16N39/00 ,  F16N2210/12 ,  F23R3/26 ,  F23R3/50 ,  F23R2900/00

Abstract: A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

公开(公告)号：US20210324761A1

公开(公告)日：2021-10-21

申请号：US16849523

申请日：2020-04-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy BOUCHARD ,  Louis BRILLON

IPC: F01D25/18

Abstract: A gas turbine engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.

公开(公告)号：US20140150449A1

公开(公告)日：2014-06-05

申请号：US13690083

申请日：2012-11-30

Applicant: Pratt & Whitney Canada Corp.

Inventor： John Watson ,  Guy BOUCHARD ,  Daniel BLAIS

IPC: F02C7/18 ,  F02C7/36

CPC classification number: F01D5/026 ,  F01D25/125 ,  F01D25/16

Abstract: A gas turbine engine including a compressor rotor and a turbine rotor connected by a compressor shaft portion connected to the compressor rotor and a turbine shaft portion connected to the turbine rotor. The compressor shaft portion and the turbine shaft portion are connected axially together by a shaft coupling, between the compressor rotor and the turbine rotor, and at least a bearing rotatably coupled to the compressor shaft portion adjacent the shaft coupling. The compressor shaft and/or the turbine shaft are provided with openings permitting cooling air to enter air passages in the area of the shaft coupling and surrounding the end of the turbine shaft portion, in order to dissipate heat originating at the turbine rotor and thus reducing the thermal stresses at the bearing.

Abstract translation: 一种燃气涡轮发动机，包括压缩机转子和通过与压缩机转子连接的压缩机轴部分连接的涡轮转子和连接到涡轮转子的涡轮轴部分。 压缩机轴部分和涡轮机轴部分通过轴联轴器在压缩机转子和涡轮机转子之间轴向连接在一起，并且至少一个轴承可旋转地联接到邻近轴联接器的压缩机轴部分。 压缩机轴和/或涡轮轴设置有允许冷却空气进入轴联接区域中并且围绕涡轮机轴部分的端部的空气通道的开口，以便耗散在涡轮机转子处产生的热量并因此减小 轴承处的热应力。