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    VARIABLE VANE AIRFOIL WITH RECESS TO ACCOMMODATE PROTUBERANCE
    11.
    发明公开
    VARIABLE VANE AIRFOIL WITH RECESS TO ACCOMMODATE PROTUBERANCE 审中-公开

    公开(公告)号：US20240052852A1

    公开(公告)日：2024-02-15

    申请号：US17884167

    申请日：2022-08-09

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Jason Nichols ,  David Batch ,  Daniel Poick

    IPC: F04D29/56 ,  F04D29/54

    CPC classification number: F04D29/563 ,  F04D29/547 ,  F05D2240/12

    Abstract: A gas turbine engine apparatus includes an engine flowpath, a protuberance and a variable vane. The protuberance projects into the engine flowpath. The variable vane extends across the engine flowpath. 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. A recess extends spanwise into the airfoil from the first end. The airfoil, at the first end, is spaced from the protuberance when the variable vane is in the first position. The airfoil, at the first end, is aligned with the protuberance and the protuberance projects into the recess when the variable vane is in the second position.

    TURBO-MACHINERY ROTORS WITH ROUNDED TIP EDGE
    13.
    发明申请
    TURBO-MACHINERY ROTORS WITH ROUNDED TIP EDGE 审中-公开
    涡轮机械转轮带有尖头边缘

    公开(公告)号：US20140260324A1

    公开(公告)日：2014-09-18

    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 ,  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.

    Abstract translation: 用于燃气涡轮发动机的转子包括多个径向延伸的叶片，每个叶片具有限定外部尖端表面的远程叶片尖端和限定在相对的压力和吸力侧翼面之间的前缘。 护罩周向地围绕转子，并且护罩的内表面和刀片的外尖端表面之间的径向距离限定了它们之间的径向顶端间隙。 每个叶片的尖端具有形成在外端头表面和压力侧翼型件表面之间的交叉点处的压力侧边缘，以及形成在外端头表面和压力侧翼型件表面之间的交叉处的吸力侧边缘。 吸力侧边缘具有比压力侧边缘更大的曲率半径，从而减少通过径向顶端间隙的尖端泄漏量。

    Gas turbine engine rotor blade geometry and method for selecting same
    14.
    发明授权
    Gas turbine engine rotor blade geometry and method for selecting same 有权

    公开(公告)号：US12215597B1

    公开(公告)日：2025-02-04

    申请号：US18424383

    申请日：2024-01-26

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Anthony Bruni ,  Jason Nichols ,  Ramy Rashad ,  Mohammadreza Amiralaei

    IPC: F01D5/14 ,  F04D29/28

    Abstract: An aircraft propulsion system includes a bladed rotor configured for rotation about a rotational axis. A rotor blade of the bladed rotor of rotor blades includes a blade body. The blade body has a blade span extending between and to a base end and a tip end. The blade body has a blade chord extending between and to a leading edge and a trailing edge. The blade body forms a pressure side surface and a suction side surface. The blade body forms a recess at the pressure side surface. The recess includes a recess surface portion forming a portion of the pressure side surface. The recess surface portion has a recess height. The recess height is greater than or equal to a Y-value of 0.025 for a normalized two-dimensional curve of a surface profile of the recess surface portion taken along a Y-Z plane orthogonal to the rotational axis for a recess span.

    AIR INTAKE PLENUM WITH STRUTS
    15.
    发明公开
    AIR INTAKE PLENUM WITH STRUTS 审中-公开

    公开(公告)号：US20230332540A1

    公开(公告)日：2023-10-19

    申请号：US17723012

    申请日：2022-04-18

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Hien Duong ,  Jason Nichols

    IPC: F02C7/042 ,  F02C7/052

    CPC classification number: F02C7/042 ,  F02C7/052 ,  F05D2260/607

    Abstract: An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.

    DIFFUSER PIPE WITH EXIT FLARE
    16.
    发明公开
    DIFFUSER PIPE WITH EXIT FLARE 审中-公开

    公开(公告)号：US20230193819A1

    公开(公告)日：2023-06-22

    申请号：US17967501

    申请日：2022-10-17

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Jason Nichols ,  Ryan Perera

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

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

    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.

    Diffuser pipe with asymmetry
    17.
    发明授权
    Diffuser pipe with asymmetry 有权

    公开(公告)号：US11136993B2

    公开(公告)日：2021-10-05

    申请号：US16374046

    申请日：2019-04-03

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Hien Duong ,  Peter Townsend ,  Jason Nichols

    IPC: F04D29/44

    Abstract: A compressor diffuser for a gas turbine engine is described which includes diffuser pipes having a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction, 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. A first curved side wall of the tubular body along the second portion is shorter than a second curved side wall of the tubular body along the second portion. The second portion of the tubular body has a cross-sectional profile defined in a plane normal to the pipe center axis. The first curved side wall of the cross-sectional profile has a smaller radius than a radius of the second curved side wall of the cross-sectional profile.

    COMPRESSOR SHROUD REVERSE BLEED HOLES
    20.
    发明申请
    COMPRESSOR SHROUD REVERSE BLEED HOLES 有权
    压缩机SHROUD反向BLEED HOLES

    公开(公告)号：US20140286746A1

    公开(公告)日：2014-09-25

    申请号：US13783773

    申请日：2013-03-04

    Applicant: Pratt & Whitney Canada Corp.

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

    IPC: F02C6/08 ,  F04D27/00

    CPC classification number: F02C9/18 ,  F01D5/145 ,  F02C3/04 ,  F04D27/023 ,  F04D29/526 ,  F04D29/682 ,  Y02T50/671

    Abstract: A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface. Bleed air removed from the annular gas flow passage flows through the bleed holes from the inlet to the outlet ends. The outlet end of each bleed hole is located circumferentially upstream of the inlet end relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor.

    Abstract translation: 燃气涡轮发动机压缩机包括限定中心旋转轴线的转子和突出到环形压缩机气体流动通道中的多个叶片，以及周向围绕转子并具有与叶片尖端相邻的径向内表面的护罩。 排泄孔延伸穿过邻近叶片尖端的护罩，每个排放孔具有设置在护罩径向内表面中的入口端和设置在护罩径向外表面中的出口端。 从环形气体流动通道移除的排出空气从入口流到出口端。 每个排放孔的出口端相对于由转子的旋转方向驱动的环形气体流动通道中的旋转流动方向位于入口端的周向上方。

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