公开(公告)号：US20190257214A1

公开(公告)日：2019-08-22

申请号：US15898725

申请日：2018-02-19

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Maksim PANKRATOV ,  Kenneth PARKMAN

IPC分类号： F01D25/18 ,  F01D25/16 ,  F04D29/059 ,  F02C7/06

摘要： There is disclosed a seal and bearing assembly having a bearing received within a housing. The bearing is disposed radially outwardly of a shaft and having an inner portion and an outer portion. The outer portion has a protrusion extending at least in an axial direction. An outer diameter of the outer portion is sized to provide a radial gap between the outer diameter and the housing section. The gap receives a film of lubricant for damping movements of the bearing relative to the housing section. A sealing member has a rotating portion configured for rotation with the shaft radially spaced apart from a static portion defined by the protrusion of the bearing outer portion. There is also disclosed a method of operating such an assembly.

公开(公告)号：US20230358145A1

公开(公告)日：2023-11-09

申请号：US17662143

申请日：2022-05-05

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Hervé TURCOTTE ,  Kenneth PARKMAN ,  Oleg MORENKO ,  Nicholas GUGLIELMIN ,  Gavin KISUN ,  Ryan MISKIE

IPC分类号： F01D9/06 ,  F01D25/16

CPC分类号： F01D9/065 ,  F01D25/162 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/53 ,  F05D2260/60

摘要： An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

公开(公告)号：US20180363913A1

公开(公告)日：2018-12-20

申请号：US15628257

申请日：2017-06-20

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Guy BOUCHARD ,  Kenneth PARKMAN

IPC分类号： F23R3/48 ,  F23R3/50 ,  F23R3/26

CPC分类号： 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

摘要： 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：US20220170419A1

公开(公告)日：2022-06-02

申请号：US17109830

申请日：2020-12-02

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Oleg MORENKO ,  Kenneth PARKMAN

IPC分类号： F02C7/06 ,  F23R3/00

摘要： The gas turbine engine combustor can have a gas generator case having a first coefficient of thermal expansion, a liner inside the gas generator case, the liner delimiting a combustion chamber, a service tube extending inside the gas generator case, outside the liner, the service tube having a second coefficient of thermal expansion, the second coefficient of thermal expansion being higher than the first coefficient of thermal expansion.

公开(公告)号：US20230130641A1

公开(公告)日：2023-04-27

申请号：US17510804

申请日：2021-10-26

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Kenneth PARKMAN ,  Daniel ALECU

IPC分类号： F01D25/20 ,  F01M1/02

摘要： Lubrication systems of an aircraft engine and associated methods are provided. The lubrication system includes a chamber having a fluid inlet for receiving lubricating fluid into the chamber, and a fluid outlet for draining the lubricating fluid from the chamber. The fluid outlet is disposed on a wall defining part of the chamber. A rotor is disposed inside the chamber and interacts with the lubricating fluid inside the chamber. The rotor is rotatable in a rotation direction about a rotation axis. A perforated baffle is disposed in the chamber for interacting with the lubricating fluid inside the chamber. The perforated baffle includes a base attached to the wall of the chamber. The base of the perforated baffle is disposed at an angular position preceding the fluid outlet relative to the rotation direction of the rotor.

公开(公告)号：US20210047937A1

公开(公告)日：2021-02-18

申请号：US16553776

申请日：2019-08-28

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Kenneth PARKMAN ,  Maksim PANKRATOV

IPC分类号： F01D11/02 ,  F02C7/28

摘要： A labyrinth seal assembly for a gas turbine engine having a rotatable shaft. The labyrinth seal assembly has: a housing defining a cavity for receiving a lubricant; a labyrinth seal between the housing and the rotatable shaft of the gas turbine engine, the labyrinth seal having a seal rotor securable to the rotatable shaft and a seal stator secured to the housing; and an insulation layer between the seal stator and the housing, the insulation layer composed of a material different than those used for the seal stator and the housing.