公开(公告)号：US10954820B2

公开(公告)日：2021-03-23

申请号：US15884775

申请日：2018-01-31

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Alexander Smith

IPC: F01D25/18 ,  F16J15/44 ,  F16J15/28 ,  F02C7/28 ,  F02C7/06

Abstract: There is provided a non-contacting seal assembly for a gas turbine engine, having a housing that houses a sealing ring; and a counter component cooperating with the sealing ring. The sealing ring and the counter component are rotatable relative to each other about a central axis and define sealing faces circumferentially extending around the central axis. The sealing faces face each other and are spaced apart from each other by a controlled gap. At least one of the sealing faces is coated with a non-abradable material. A method of operating a non-contacting seal assembly is also provided.

公开(公告)号：US11421597B2

公开(公告)日：2022-08-23

申请号：US16656750

申请日：2019-10-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Gabriel Naccache ,  Christopher Gover ,  Alexander Smith ,  Alain Martel ,  Matthieu Boudreau

IPC: F02C7/12 ,  F02C7/22

Abstract: A tangential on-board injector (TOBI) having: a body defining an annular passageway, discharge nozzles; a rotating component configured to be mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; and flow passages circumferentially distributed about the axis of rotation and in fluid communication with the nozzles and the seal, the flow passages located upstream of the seal relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles, each of the flow passages extending along a respective passage axis, the passage axis of at least one of the flow passages having a tangential component at an outlet of the at least one of the flow passages that is different than a tangential component of an exit flow axis of at least one of the plurality of discharge nozzles.

公开(公告)号：US08616777B1

公开(公告)日：2013-12-31

申请号：US13678803

申请日：2012-11-16

Applicant: Pratt & Whitney Canada Corp.

Inventor： Alexander Smith ,  Haw On Tam

IPC: F16C33/66

CPC classification number: F16C33/586 ,  F16C19/26 ,  F16C33/6677 ,  F16C2360/23

Abstract: An inner ring for a bearing assembly with an inner surface having a plurality of circumferentially spaced axial slots defined therein each having a flat axially extending bottom wall and a plurality of circumferentially spaced partial circumferential slots defined therein each intersecting one of the axial slots and extending circumferentially therefrom around a respective portion of a circumference of the inner surface, shoulder radial holes extending therethrough each from a respective one of the circumferential slots to a corresponding one of the shoulders, and race radial holes extending therethrough each from a respective one of the circumferential slots to a corresponding corner of the inner race. The radial holes are circumferentially offset from the axial slots. A bearing assembly and a method of lubricating such an assembly are also discussed.

Abstract translation: 一种用于轴承组件的内圈，内表面具有限定在其中的多个周向间隔开的轴向槽，每个轴向槽具有平坦的轴向延伸的底壁和限定在其中的多个周向间隔开的部分圆周槽，每个槽与所述轴向槽中的一个相交并且沿周向延伸 从其周围的内表面的圆周的相应部分，肩部径向孔从其中的相应的一个周向狭槽延伸到相应的一个肩部，以及从相应的一个周向槽延伸穿过的跑道径向孔 到内圈的相应角落。 径向孔从轴​​向槽周向偏移。 还讨论了轴承组件和润滑这种组件的方法。

公开(公告)号：US11815020B2

公开(公告)日：2023-11-14

申请号：US17813745

申请日：2022-07-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Gabriel Naccache ,  Christopher Gover ,  Alexander Smith ,  Alain Martel ,  Matthieu Boudreau

IPC: F01D5/08 ,  F02C7/12 ,  F02C7/22

CPC classification number: F02C7/12 ,  F01D5/081 ,  F01D5/082 ,  F02C7/22 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/55

Abstract: A tangential on-board injector (TOBI), comprising: a body defining an annular passageway to receive cooling air, the TOBI defining a plurality of discharge nozzles; a rotating component mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; a plurality of vanes circumferentially distributed about the axis of rotation and located downstream of the plurality of discharge nozzles relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles and upstream of the seal; and flow passages defined between the plurality of vanes, a flow passage of the flow passages extending along a passage axis, the passage axis having a tangential component at an outlet of the flow passage that is different than a tangential component of an exit flow axis of a nozzle of the plurality of discharge nozzles.

公开(公告)号：US11306593B2

公开(公告)日：2022-04-19

申请号：US16558951

申请日：2019-09-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Acher-Igal Abenhaim ,  Vincent Paradis ,  Marc-Antoine Mailloux-Labrousse ,  Alexander Smith

IPC: F01D5/06 ,  F01D25/00

Abstract: A gas turbine engine comprising: a shaft about an axis; a first turbine assembly mounted to the shaft, a first flow path and a second flow path extending through first turbine assembly along the axis. The second flow path is located radially inward of the first flow path relative to the axis. A second turbine assembly is about the axis downstream of the first turbine assembly, with a gap defined between the first turbine assembly and the second turbine assembly, the gap in fluid communication with the first flow path and the second flow path. A washer is downstream of the first turbine assembly. The washer has an annular body including a deflector between the first turbine assembly and the second turbine assembly, the deflector obstructing the first flow path and extending toward the second flow path.

公开(公告)号：US11293295B2

公开(公告)日：2022-04-05

申请号：US16570066

申请日：2019-09-13

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Alexander Smith ,  Pierre-Yves Legare

IPC: F01D11/02 ,  F01D11/00 ,  F04D29/10 ,  F16J15/447

Abstract: An aircraft engine having a shaft, an engine casing, at least one bearing located between the shaft and the engine casing, the engine casing defining a bearing cavity containing the at least one bearing, an air distribution system configured to inject compressed air to the bearing cavity to in use provide a sealing air flow entering the bearing cavity, and a labyrinth seal having a seal rotor and a seal stator, fins extending from one of the seal rotor and the seal stator toward the other of the seal rotor and the seal stator, at least one of the fins extending in an angled upstream direction relative to a direction of the sealing air flow.