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公开(公告)号：US20220135242A1
公开(公告)日：2022-05-05
申请号：US17089564
申请日：2020-11-04
Applicant: Honeywell International Inc.
Inventor： Richard David Conner , Ryan Cox , Josef Merki , Brian Larsen
Abstract: A ram air turbine rotor comprises at least one intra-flow path shroud structure coupled between rotor blades, along a radial position between a support disc and an outer rim. The shroud structure includes shroud sectors each coupled between a respective pair of blades. The sectors each include a first edge adjacent to leading edges of the respective pair of blades, the first edge including a first curved segment, and a second edge adjacent to trailing edges of the respective pair of blades, the second edge including a second curved segment. The curved segments are each partially defined by a respective ellipse having a semi-major axis and a semi-minor axis. The semi-major axis is a portion of a spanwise distance between the respective pair of blades. The semi-minor axis is a portion of an axial distance between the leading edge of one blade and the trailing edge of an adjacent blade.
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公开(公告)号：US20200240435A1
公开(公告)日：2020-07-30
申请号：US16681303
申请日：2019-11-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Timothy Gentry , Richard David Conner
Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each having a button forward edge portion and the airfoil including leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local aft sweep at the tip, thereby forming a locally swept tip of the leading edge thereat. The button forward edge portion of the outer button is substantially vertically aligned with the locally swept tip of the leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
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公开(公告)号：US12025026B2
公开(公告)日：2024-07-02
申请号：US18365118
申请日：2023-08-03
Applicant: Honeywell International Inc.
Inventor： Richard David Conner , Ryan Cox , Josef Merki , Brian Larsen
CPC classification number: F01D5/10 , F01D5/022 , F01D5/03 , F01D5/143 , F03D1/0633 , F03D9/32 , F05B2220/31 , F05B2240/33 , F05B2240/923 , F05B2250/14 , F05B2250/141 , F05D2240/24
Abstract: A ram air turbine rotor comprises at least one intra-flow path shroud structure coupled between rotor blades, along a radial position between a support disc and an outer rim. The shroud structure includes shroud sectors each coupled between a respective pair of blades. The sectors each include a first edge adjacent to leading edges of the respective pair of blades, the first edge including a first curved segment, and a second edge adjacent to trailing edges of the respective pair of blades, the second edge including a second curved segment. The curved segments are each partially defined by a respective ellipse having a semi-major axis and a semi-minor axis. The semi-major axis is a portion of a spanwise distance between the respective pair of blades. The semi-minor axis is a portion of an axial distance between the leading edge of one blade and the trailing edge of an adjacent blade.
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公开(公告)号：US20180094645A1
公开(公告)日：2018-04-05
申请号：US15685038
申请日：2017-08-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Timothy Gentry , Richard David Conner
CPC classification number: F04D29/544 , F01D5/141 , F01D11/005 , F01D17/162 , F04D29/563 , F05D2240/121 , F05D2250/70 , Y02T50/673
Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root, thereby forming a locally swept root of the leading edge thereat. The button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
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公开(公告)号：US09784285B2
公开(公告)日：2017-10-10
申请号：US14485163
申请日：2014-09-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Timothy Gentry , Richard David Conner
CPC classification number: F04D29/544 , F01D5/141 , F01D11/005 , F01D17/162 , F04D29/563 , F05D2240/121 , F05D2250/70 , Y02T50/673
Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
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Patent Agency Ranking
公开(公告)号：US11156092B2
公开(公告)日：2021-10-26
申请号：US16269804
申请日：2019-02-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Richard David Conner , Michael T. Barton , Jeffrey W. Gluck , Nick Nolcheff
IPC: F01D5/06
Abstract: A method of manufacturing a multistage axial-centrifugal compressor for a gas turbine engine and a multistage axial-centrifugal compressor that includes a series of axial compressor stages each having a rotor mounted to a common shaft positioned upstream from a centrifugal compressor stage mounted to the common shaft. The method includes determining an operational rotor tip speed for each of the axial stages. The method includes comparing the operational rotor tip speed to a threshold range value and determining to machine an airfoil of the rotor for at least one of the axial stages by an arbitrary manufacturing approach based on the operational rotor tip speed as greater than the threshold range value. The method includes determining to machine an airfoil of the rotor for at least one of the axial stages by a flank manufacturing approach based on the operational rotor tip speed as less than the threshold range value.
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公开(公告)号：US10527060B2
公开(公告)日：2020-01-07
申请号：US15685038
申请日：2017-08-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Timothy Gentry , Richard David Conner
Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root, thereby forming a locally swept root of the leading edge thereat. The button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
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8.发明申请公开(公告)号：US20180216632A1
公开(公告)日：2018-08-02
申请号：US15420717
申请日：2017-01-31
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Richard David Conner , Bruce David Reynolds , Timothy Gentry , Peter Hall
CPC classification number: F04D29/563 , F01D9/041 , F01D11/005 , F01D17/162 , F04D27/002 , F04D29/023 , F04D29/542 , F04D29/644 , F05D2220/32 , F05D2240/12 , F05D2240/122
Abstract: Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly. By virtue of the translational movement of the translating vane structures, a reduction in the clearances between the vane bodies and neighboring flow assembly surfaces can be realized to reduce end gap leakage and boost device performance.
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公开(公告)号：US20160238018A1
公开(公告)日：2016-08-18
申请号：US14623761
申请日：2015-02-17
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Richard David Conner , Michael Todd Barton , Yoseph Gebre-Giorgis , Harry Lester Kington , John Repp
CPC classification number: F04D29/284 , F01D5/225 , F01D9/04 , F02C3/09 , F05D2250/38 , F05D2260/941 , Y02T50/671
Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.
Abstract translation: 如同包含前掠式叶轮的燃气涡轮发动机的实施例一样，提供了前掠式叶轮的实施例。 在一个实施例中，燃气涡轮发动机包括安装在轴上的轴和向前扫掠的叶轮。 前掠式叶轮又包括内侧叶轮部分，外侧叶轮部分，其包围内侧叶轮部分，以及多个轮毂流动路径，其沿前掠式叶轮从内侧叶轮部分延伸到外侧叶轮部分。 多个轮毂流动路径各自具有沿着与流路出口相切的直线沿向前方向倾斜的流路出口。
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公开(公告)号：US20200256192A1
公开(公告)日：2020-08-13
申请号：US16269804
申请日：2019-02-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Richard David Conner , Michael T. Barton , Jeffrey W. Gluck , Nick Nolcheff
IPC: F01D5/06
Abstract: A method of manufacturing a multistage axial-centrifugal compressor for a gas turbine engine and a multistage axial-centrifugal compressor that includes a series of axial compressor stages each having a rotor mounted to a common shaft positioned upstream from a centrifugal compressor stage mounted to the common shaft. The method includes determining an operational rotor tip speed for each of the axial stages. The method includes comparing the operational rotor tip speed to a threshold range value and determining to machine an airfoil of the rotor for at least one of the axial stages by an arbitrary manufacturing approach based on the operational rotor tip speed as greater than the threshold range value. The method includes determining to machine an airfoil of the rotor for at least one of the axial stages by a flank manufacturing approach based on the operational rotor tip speed as less than the threshold range value.
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