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公开(公告)号：US20190072034A1
公开(公告)日：2019-03-07
申请号：US16177765
申请日：2018-11-01
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Farid ABRARI , Peter TOWNSEND
Abstract: An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.
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公开(公告)号：US20170268529A1
公开(公告)日：2017-09-21
申请号：US15616302
申请日：2017-06-07
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Karl HEIKURINEN , Peter TOWNSEND
IPC: F04D29/38 , B23K20/12 , F01D5/14 , F01D5/30 , F01D5/34 , F02K3/06 , F04D29/02 , F04D29/32 , F04D29/34 , F04D29/64 , B23K101/00
CPC classification number: F04D29/384 , B23K20/129 , B23K2101/001 , F01D5/14 , F01D5/3061 , F01D5/34 , F02K3/06 , F04D29/023 , F04D29/321 , F04D29/324 , F04D29/329 , F04D29/34 , F04D29/388 , F04D29/644 , F05D2230/239 , F05D2260/40 , Y10T29/49245
Abstract: A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.
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公开(公告)号：US20170204876A1
公开(公告)日：2017-07-20
申请号：US15410060
申请日：2017-01-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Karan ANAND , Peter TOWNSEND , Tibor URAC , Terry BROWNRIDGE
CPC classification number: F04D29/526 , F04D29/164 , F04D29/324 , F04D29/644 , F04D29/685 , F05D2250/294 , F05D2250/61
Abstract: A gas turbine engine is described having a rotor with a plurality of rotor blades each extending radially between a blade root to a blade tip and axially between a leading edge and a trailing edge. An annular casing body housing the rotor blades includes an abradable segment of the inner surface facing the blade tips and having an abradable member. The abradable segment having one or more annular grooves, extending into the casing body from an inner surface thereof, and including an edge groove axially aligned with and facing the leading edge or the trailing edge of the rotor blades. The edge groove extends axially between a first position on the inner surface upstream of the leading edge or the trailing edge, and a second position on the inner surface downstream of the leading edge or the trailing edge.
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公开(公告)号：US20210372434A1
公开(公告)日：2021-12-02
申请号：US17402702
申请日：2021-08-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Hong YU , Peter TOWNSEND
Abstract: Am aircraft engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed.
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公开(公告)号：US20190107123A1
公开(公告)日：2019-04-11
申请号：US15726819
申请日：2017-10-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
Abstract: A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.
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Patent Agency Ranking
公开(公告)号：US20170241432A1
公开(公告)日：2017-08-24
申请号：US15436091
申请日：2017-02-17
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ignatius THERATIL , Krishna Prasad BALIKE , Aldo ABATE , Sean KELLY , Peter TOWNSEND , Ronald DUTTON , Anthony BROWN , Paul STONE , Myron KLEIN , Milica KOJOVIC , Robert VENDITTI
CPC classification number: F04D29/327 , F02K3/06 , F04D19/002 , F04D21/00 , F04D29/324 , F04D29/666 , F05D2220/36 , F05D2240/302 , F05D2240/303 , F05D2240/307 , F05D2260/961
Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.
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公开(公告)号：US20210260706A1
公开(公告)日：2021-08-26
申请号：US17318414
申请日：2021-05-12
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ian A. MACFARLANE , Peter TOWNSEND , Hong YU
Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.
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公开(公告)号：US20180156235A1
公开(公告)日：2018-06-07
申请号：US15370497
申请日：2016-12-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Yau-Wai LI , Peter TOWNSEND , Ronald DUTTON , Bernadette MASON
CPC classification number: F04D29/542 , F01D9/041 , F02K3/06 , F04D29/666 , F05D2230/60
Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.
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公开(公告)号：US20160084265A1
公开(公告)日：2016-03-24
申请号：US14493785
申请日：2014-09-23
Applicant: Pratt & Whitney Canada Corp.
Inventor： Hong YU , Peter TOWNSEND
CPC classification number: F04D29/542 , F02C7/042 , F02C7/045 , F02C7/047 , F04D29/544 , F04D29/563 , F04D29/584 , F04D29/5853 , F04D29/681 , F05D2260/961
Abstract: A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed.
Abstract translation: 涡轮风扇发动机包括围绕入口流动路径的轴向延伸的入口壁。 入口壁和邻近风扇的内壁之间的径向距离限定了入口流动路径的下游高度。 多个叶片围绕入口周向间隔开，每个叶片从入口壁径向向内延伸，每个叶片的尖端与限定叶片的最大高度的入口壁之间的最大径向距离。 叶片的最大高度为流路下游高度的50％以下。 在另一个实施例中，叶片的最大高度是最大风扇叶片跨度的至多50％。 还讨论了减少风扇叶片尖端的相对马赫数的方法。
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公开(公告)号：US20140356159A1
公开(公告)日：2014-12-04
申请号：US13687540
申请日：2012-11-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Kari HEIKURINEN , Peter TOWNSEND
IPC: F02K3/06
CPC classification number: F04D29/384 , B23K20/129 , B23K2101/001 , F01D5/14 , F01D5/3061 , F01D5/34 , F02K3/06 , F04D29/023 , F04D29/321 , F04D29/324 , F04D29/329 , F04D29/34 , F04D29/388 , F04D29/644 , F05D2230/239 , F05D2260/40 , Y10T29/49245
Abstract: A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge. A hub radius (RHUB) is the radius of the leading edge at the hub relative to a centerline of the fan. A tip radius (RTIP) is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is at least less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than or equal to 0.25.
Abstract translation: 一种用于涡轮风扇燃气涡轮发动机的风扇，风扇包括转子毂和多个径向延伸的与轮毂一体形成的叶片转子的径向延伸的风扇叶片。 每个风扇叶片定义一个前缘。 轮毂半径（RHUB）是轮毂相对于风扇中心线的前缘的半径。 尖端半径（RTIP）是风扇叶片尖端相对于风扇中心线的前缘的半径。 轮毂半径与顶端半径（RHUB / RTIP）的比率至少小于0.29。 在一个具体实施方案中，该比率在0.25和0.29之间。 在另一具体实施方案中，该比率小于或等于0.25。
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