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公开(公告)号：US11965459B2
公开(公告)日：2024-04-23
申请号：US17723012
申请日：2022-04-18
Applicant: Pratt & Whitney Canada Corp.
Inventor： Hien Duong , Jason Nichols
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.
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公开(公告)号：US11421702B2
公开(公告)日：2022-08-23
申请号：US16546781
申请日：2019-08-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jason Nichols
Abstract: An impeller for a centrifugal compressor, the impeller comprising: a hub defining a rotation axis about which the impeller is rotatable; and a vane extending from the hub, the vane having a leading edge, a trailing edge, and a chord defined therebetween, a pressure side of the vane and a suction side of the vane opposite the pressure side, a vane thickness defined transversely between the pressure side and the suction side, the vane thickness reducing over at least a downstream 40% of the chord, the vane thickness having a trailing edge thickness value at the trailing edge of between 40% and 80% of a maximum thickness value of the vane thickness.
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公开(公告)号：US11143201B2
公开(公告)日：2021-10-12
申请号：US16354292
申请日：2019-03-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Hien Duong , Jason Nichols
IPC: F04D29/44
Abstract: A gas turbine engine for an aircraft having a centrifugal compressor including an impeller with impeller blades extending from a hub, the impeller mounted for rotation about a central longitudinal axis within an outer shroud. A main flow passage wall is located on a shroud side near the impeller exit, the main flow passage wall separating a cavity disposed on the shroud side from the main flow passage. One or more apertures are defined through the main flow passage wall and extending along a respective aperture axis between the cavity and the main flow passage. The apertures have a main flow passage side opening located radially outward from the impeller exit. The aperture axis is disposed at a radial angle relative to the central longitudinal axis.
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公开(公告)号：US20240271563A1
公开(公告)日：2024-08-15
申请号：US18642138
申请日：2024-04-22
Applicant: Pratt & Whitney Canada Corp.
Inventor： Hien Duong , Jason Nichols
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.
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公开(公告)号：US11125154B2
公开(公告)日：2021-09-21
申请号：US16674368
申请日：2019-11-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jason Nichols , Ignatius Theratil , Mohammadreza Amiralaei
Abstract: The centrifugal impeller can have a hub and a plurality of blades, each of the blades having a span extending from the hub to a tip edge, camber lines extending from an inlet edge to an outlet edge between two opposite faces, including a tip camber line extending along the tip edge and a 50% span camber line extending at 50% of the span, a thickness extending between opposite faces of each blade, the tip edge having, at a location corresponding to 5% of the tip camber line, less than 15% of the maximum thickness, each of the blades having, along the 50% span camber line, a thickness reaching at least 58% of the maximum thickness and then reducing by at least 5% of the maximum thickness within 10% of the length of the 50% span camber line.
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Patent Agency Ranking
公开(公告)号：US10781705B2
公开(公告)日：2020-09-22
申请号：US16201255
申请日：2018-11-27
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jason Nichols , Thomas Veitch , Peter Townsend , Hien Duong , Guiherme Watson
Abstract: An inter-compressor case for a gas turbine engine is disclosed. The inter-compressor case comprises: an outer casing and an inner casing radially spaced apart relative to a longitudinal axis; a gas path extending from a plurality of radial inlets arranged in a circumferentially spaced apart array around the outer casing to an annular outlet defined by an axially extending downstream portion of the outer casing and an axially extending downstream portion of the inner casing; a plurality of struts having a gas path surface extending across the gas path between the outer casing and the inner casing; and a plurality of flow separators extending from the adjacent radial inlets. The flow separators have trailing edges disposed upstream of the annular outlet and include a plurality of full length flow separators and a plurality of truncated flow separators.
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公开(公告)号：US09500084B2
公开(公告)日：2016-11-22
申请号：US13775693
申请日：2013-02-25
Applicant: Pratt & Whitney Canada Corp.
Inventor： Raman Warikoo , Hien Duong , Jason Nichols , Tsukasa Yoshinaka
CPC classification number: F01D5/141 , F01D5/043 , F04D29/284
Abstract: An impeller for increasing the pressure of a fluid circulating in an annular fluid path, the impeller comprising: a plurality of centrifugal compressor vanes circumferentially interspaced around the axis of the annular fluid path, the plurality of compressor vanes extending from an axially-oriented inlet to a radially-oriented outlet, and each having an inner edge and a free edge, the free edge of the plurality of compressor vanes coinciding with an outer limit of the annular fluid path, and a hub having a solid-of-revolution shape centered around an axis, the hub having an outer hub surface forming an inner limit to the annular fluid path and to which the inner edge of the plurality of centrifugal vanes is secured, the outer hub surface having a portion which leans forward, forming an axial recess therein.
Abstract translation: 一种用于增加在环形流体路径中循环的流体的压力的叶轮，所述叶轮包括：围绕所述环形流体路径的轴线周向间隔的多个离心压缩机叶片，所述多个压缩机叶片从轴向定向的入口延伸到 径向定向的出口，并且每个具有内边缘和自由边缘，多个压缩机叶片的自由边缘与环形流体路径的外部极限相重合，并且具有围绕 所述轮毂具有形成所述环形流体路径的内部极限的外部毂表面，并且所述多个离心叶片的内部边缘被固定到所述外部毂表面上，所述外部毂表面具有向前倾斜的部分，在其中形成轴向凹部 。
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公开(公告)号：US20140241901A1
公开(公告)日：2014-08-28
申请号：US13775693
申请日：2013-02-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Raman Warikoo , Hien Duong , Jason Nichols , Tsukasa Yoshinaka
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/043 , F04D29/284
Abstract: An impeller for increasing the pressure of a fluid circulating in an annular fluid path, the impeller comprising: a plurality of centrifugal compressor vanes circumferentially interspaced around the axis of the annular fluid path, the plurality of compressor vanes extending from an axially-oriented inlet to a radially-oriented outlet, and each having an inner edge and a free edge, the free edge of the plurality of compressor vanes coinciding with an outer limit of the annular fluid path, and a hub having a solid-of-revolution shape centered around an axis, the hub having an outer hub surface forming an inner limit to the annular fluid path and to which the inner edge of the plurality of centrifugal vanes is secured, the outer hub surface having a portion which leans forward, forming an axial recess therein.
Abstract translation: 一种用于增加在环形流体路径中循环的流体的压力的叶轮，所述叶轮包括：围绕所述环形流体路径的轴线周向间隔的多个离心压缩机叶片，所述多个压缩机叶片从轴向定向的入口延伸到 径向定向的出口，并且每个具有内边缘和自由边缘，多个压缩机叶片的自由边缘与环形流体路径的外部极限相重合，并且具有围绕 所述轮毂具有形成所述环形流体路径的内部极限的外部毂表面，并且所述多个离心叶片的内部边缘被固定到所述外部毂表面上，所述外部毂表面具有向前倾斜的部分，在其中形成轴向凹部 。
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公开(公告)号：US12078189B2
公开(公告)日：2024-09-03
申请号：US17884167
申请日：2022-08-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Jason Nichols , David Batch , Daniel Poick
CPC classification number: F04D29/563 , F01D5/141 , F01D5/147 , F01D9/041 , F01D17/162 , F04D29/547 , F01D7/00 , F05D2240/12 , F05D2240/128
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.
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公开(公告)号：US11970948B2
公开(公告)日：2024-04-30
申请号：US17884184
申请日：2022-08-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Jason Nichols
CPC classification number: F01D17/162 , F01D5/141 , F01D5/147 , F01D7/00 , F01D9/041 , 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.
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