公开(公告)号：US12018583B2

公开(公告)日：2024-06-25

申请号：US16692241

申请日：2019-11-22

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hien Duong ,  Jason Nichols

IPC: F01D5/14 ,  F02K3/06 ,  F04D29/32 ,  F04D29/38

CPC classification number: F01D5/141 ,  F02K3/06 ,  F04D29/324 ,  F04D29/384 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/70

Abstract: An impeller having a hub, blades extending from the hub along respective spans from roots to tips, the blades extending along respective chords from leading edges to trailing edges, the leading edge of at least one of the blades having a cutback section defining a sweep at the root, the cutback section extending in a spanwise direction from the hub to a location at least about 5% of the span from the hub of the at least one of the blades, and the cutback section extending in a chordwise direction along at least about 5% of the chord of the at least one of the blades.

公开(公告)号：US20240052754A1

公开(公告)日：2024-02-15

申请号：US17884184

申请日：2022-08-09

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jason Nichols

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F05D2240/128

Abstract: A gas turbine engine apparatus includes a variable vane. The variable vane includes a pivot axis and an airfoil. The variable vane is configured to pivot about the pivot axis between a first position and a second position. The airfoil extends spanwise along a span line between a first end and a second end. The airfoil extends chordwise along a chord line between a leading edge and a trailing edge. The chord line is angularly offset from a reference plane containing the pivot axis by a twist angle. A first section of the airfoil is disposed at the first end. The twist angle varies as the first section extends spanwise along the span line. A second section of the airfoil is disposed spanwise between the first section and the second end. The twist angle is uniform as the second section extends spanwise along the span line.

公开(公告)号：US11859543B2

公开(公告)日：2024-01-02

申请号：US17967501

申请日：2022-10-17

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jason Nichols ,  Ryan Perera

IPC: F04D29/28 ,  F02C6/06 ,  F04D29/44 ,  F02K3/00 ,  F02C7/32

CPC classification number: F02C6/06 ,  F02C7/32 ,  F02K3/00 ,  F04D29/284 ,  F04D29/288 ,  F04D29/44 ,  F04D29/441 ,  F05D2220/32 ,  F05D2250/52 ,  F05D2250/71

Abstract: A diffuser pipe has a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction from an inlet of the tubular body, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. The tubular body has a length defined between the inlet and the pipe outlet. The tubular body has cross-sectional profiles defined in a plane normal to the pipe center axis. An area of the cross-sectional profile at the pipe outlet is at least 20% greater than an area of the cross-sectional profile at a point upstream from the pipe outlet a distance corresponding to 10% of the length of the tubular body.

公开(公告)号：US11378005B1

公开(公告)日：2022-07-05

申请号：US17124574

申请日：2020-12-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hien Duong ,  Jason Nichols

IPC: F02C3/08 ,  F04D29/68 ,  F04D27/02 ,  F04D29/44

Abstract: A diffuser for a compressor of a gas turbine engine is disclosed. The diffuser has a plurality of diffuser pipes circumferentially distributed about an axis of the compressor, each of the plurality of diffuser pipes extending from an inlet to an outlet and having a bend section between the inlet and the outlet, a low pressure side and an opposite high pressure side. A recirculation conduit defines a recirculation path from a first flow region to a second flow region in one or more of the plurality of the diffuser pipes, the first flow region having a greater static pressure than that of the second region, the recirculation conduit having a conduit inlet and a conduit outlet, at least the conduit outlet located within the low pressure side of one of the plurality of the diffuser pipes.

公开(公告)号：US11333173B2

公开(公告)日：2022-05-17

申请号：US16406659

申请日：2019-05-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jason Nichols ,  Yves Cloutier

IPC: F04D29/58 ,  F01D9/06 ,  F04D17/12

Abstract: The gas turbine engine described includes a first centrifugal compressor, a second centrifugal compressor, and intercompressor pipes extending therebetween. The intercompressor pipes fluidly interconnect an exit of a first impeller of the first centrifugal compressor and an inlet of a second impeller of the second centrifugal compressor. The intercompressor pipes have heat transfer structures on outer surfaces thereof to increase convective heat transfer.

公开(公告)号：US10859096B2

公开(公告)日：2020-12-08

申请号：US16175986

申请日：2018-10-31

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin Drolet ,  Jason Nichols

IPC: F04D29/44 ,  F01D9/06

Abstract: A compressor diffuser for a gas turbine engine includes a plurality of diffuser passages including a first portion having a radial component, a second portion having an axial component, and a curved portion fluidly connecting the first portion and the second portion. The diffuser passages having a throat located within the first portion thereof, and including a first subset of passages and a second subset of passages. The throats of the first subset of passages have a first throat area that is different than a throat area of the throats of the second subset of passages.

公开(公告)号：US10760499B2

公开(公告)日：2020-09-01

申请号：US13803368

申请日：2013-03-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hien Duong ,  Jason Nichols ,  Vijay Kandasamy

IPC: F02C7/28 ,  F01D5/20 ,  F01D5/22 ,  F01D5/14 ,  F01D11/08

Abstract: A rotor for a gas turbine engine includes a plurality of radially extending blades, each having a remote blade tip defining an outer tip surface, and a leading edge defined between opposed pressure and suction side airfoil surfaces. A shroud circumferentially surrounds the rotor, and a radial distance between an inner surface of the shroud and the outer tip surface of the blades defines a radial tip clearance gap therebetween. The tip of each of the blades has a pressure side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface, and a suction side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface. The suction side edge has a larger radius of curvature than the pressure side edge, thereby reducing the amount of tip leakage flow through the radial tip clearance gap.

公开(公告)号：US09726084B2

公开(公告)日：2017-08-08

申请号：US13803418

申请日：2013-03-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hien Duong ,  Jason Nichols ,  Peter Townsend ,  Vijay Kandasamy

IPC: F02C9/18 ,  F01D5/14 ,  F04D29/52 ,  F04D29/68 ,  F04D27/02

CPC classification number: F02C9/18 ,  F01D5/145 ,  F04D27/023 ,  F04D29/526 ,  F04D29/682

Abstract: A compressor for a gas turbine engine having a bleed air recirculation system includes a plurality of bleed holes extending through the shroud at a first axial location thereon substantially adjacent the blade tips. The bleed holes have a closed outer perimeter along their complete length. An annular bleed cavity surrounds the shroud and is in communication with outlet openings of the bleed holes. The bleed holes provide communication between the main gas flow passage and the bleed cavity. The bleed cavity includes exit passages having outlets disposed in the shroud at a second axial location which is upstream of both the first axial location and the leading edge of the blades of the rotor. Bleed air is passively bled from the main gas flow passage via the bleed holes, recirculated through the bleed cavity and re-injected back into the main gas flow passage at the second axial location.