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公开(公告)号：US10781695B1
公开(公告)日：2020-09-22
申请号：US15869912
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , William R. Edwards , Matthew R. Willett , Sean Nolan , Ernest D. Casparie
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.55-0.65 inch (14.0-16.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.76-0.86 inch (19.3-21.8 mm). The airfoil element includes at least two of a first mode with a frequency of 3335±10% Hz, a second mode with a frequency of 5715±10% Hz and a third mode with a frequency of 41797±10% Hz.
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公开(公告)号：US10533581B2
公开(公告)日：2020-01-14
申请号：US15373774
申请日：2016-12-09
Applicant: United Technologies Corporation
Inventor： William R. Edwards , Charles H. Warner
Abstract: A vane stage assembly includes an airfoil including a leading edge and a trailing edge. An inner shroud extends from the leading edge to the trailing edge for supporting the airfoil. The shroud includes a forward portion including an axial width and a forward thickness extending in a radial direction. A ratio of the forward radial thickness divided by the forward axial thickness is between 0.64 and 1.11 for defining a natural frequency of the airfoil. A gas turbine engine and method are also disclosed.
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公开(公告)号：US20180163751A1
公开(公告)日：2018-06-14
申请号：US15373774
申请日：2016-12-09
Applicant: United Technologies Corporation
Inventor： William R. Edwards , Charles H. Warner
Abstract: A vane stage assembly includes an airfoil including a leading edge and a trailing edge. An inner shroud extends from the leading edge to the trailing edge for supporting the airfoil. The shroud includes a forward portion including an axial width and a forward thickness extending in a radial direction. A ratio of the forward radial thickness divided by the forward axial thickness is between 0.64 and 1.11 for defining a natural frequency of the airfoil. A gas turbine engine and method are also disclosed.
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公开(公告)号：US20160377092A1
公开(公告)日：2016-12-29
申请号：US14753810
申请日：2015-06-29
Applicant: United Technologies Corporation
Inventor： William R. Edwards
CPC classification number: F04D29/563 , F01D25/246 , F04D29/161 , F04D29/321 , F04D29/522 , F04D29/542
Abstract: A stator vane assembly is provided. The stator vane assembly may comprise a stator vane, an outer shroud, and a spring. A first end of the stator vane may be fixed to an inner diameter (ID) surface of a vane platform. A slot may be disposed in a surface of the outer shroud, wherein a portion of the stator vane is configured to be located within the slot. In various embodiments, the stator vane may be configured to translate in a radial direction in response to a force between the stator vane and a rotor. In various embodiments, the spring may be configured to be coupled to an outer diameter (OD) surface of the vane platform, wherein the spring is configured to bias the ID surface of the vane platform toward the outer shroud.
Abstract translation: 提供定子叶片组件。 定子叶片组件可以包括定子叶片，外护罩和弹簧。 定子叶片的第一端可以固定在叶片平台的内径（ID）表面上。 槽可以设置在外护罩的表面中，其中定子叶片的一部分被配置为位于槽内。 在各种实施例中，定子叶片可构造成响应于定子叶片和转子之间的力在径向方向上平移。 在各种实施例中，弹簧可被配置为联接到叶片平台的外径（OD）表面，其中弹簧构造成将叶片平台的ID表面偏向外护罩。
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公开(公告)号：US10815826B1
公开(公告)日：2020-10-27
申请号：US15868424
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Steven J. Feigleson , Kate Hudon
IPC: F01D9/02 , F01D25/04 , F02C3/06 , F04D29/54 , F04D29/66 , F02K3/06 , F01D5/16 , F01D5/14 , F01D5/34
Abstract: An airfoil extends in a radial direction a span in a range 3.97-4.27 inch (100.9-108.6 mm). A chord length extends in a chordwise direction from a leading edge to a trailing edge at 50% span in a range 1.28-1.58 inch (32.4-40.0 mm). The airfoil includes at least two of a first mode with a frequency of 243±10% Hz, a second mode with a frequency of 374±10% Hz, a third mode with a frequency of 741±10% Hz, a fourth mode with a frequency of 1198±10% Hz, a fifth mode with a frequency of 1663±10% Hz, a sixth mode with a frequency of 2411±10% Hz, a seventh mode with a frequency of 3734±10% Hz, an eighth mode with a frequency of 6738±10% Hz and a ninth mode with a frequency of 8977±10% Hz.
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Patent Agency Ranking
公开(公告)号：US10787910B1
公开(公告)日：2020-09-29
申请号：US15868465
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Steven J. Feigleson , Kate Hudon
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.59-2.89 inch (65.7-73.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.35-1.65 inch (34.4-42.0 mm). The airfoil element includes at least two of a first mode with a frequency of 2241±10% Hz, a second mode with a frequency of 3598±10% Hz and a third mode with a frequency of 6212±10% Hz.
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公开(公告)号：US10760447B1
公开(公告)日：2020-09-01
申请号：US15869312
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Stephen W. Milks , Steven J. Feigleson , Mark A. Stephens , Joseph C. Straccia
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.84-4.14 inch (97.5-105.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.16-1.46 inch (29.5-37.1 mm). The airfoil element includes at least two of a first mode with a frequency of 326±10% Hz, a second mode with a frequency of 1252±10% Hz, a third mode with a frequency of 2475±10% Hz, a fourth mode with a frequency of 2951±10% Hz, a fifth mode with a frequency of 4356±10% Hz and a sixth mode with a frequency of 6086±10% Hz.
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公开(公告)号：US10669856B1
公开(公告)日：2020-06-02
申请号：US15869445
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , William R. Edwards , Mark David Ring , Sean Nolan , Ernest D. Casparie
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.75-0.85 inch (19.1-21.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.56-0.66 inch (14.2-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2740±10% Hz, a second mode with a frequency of 5956±10% Hz, a third mode with a frequency of 6554±10% Hz and a fourth mode with a frequency of 31959±10% Hz.
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公开(公告)号：US20190309641A1
公开(公告)日：2019-10-10
申请号：US15945409
申请日：2018-04-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Philip Robert Rioux , Mark David Ring
Abstract: A cantilevered mounted singlet vane includes a first outer shroud and a first airfoil. The first outer shroud is provided with a first body having a first body first side and a first body second side axially extending between a first body first end and a first body second end. The first outer shroud defines a first slot axially extends from the first body first end towards a first body end wall disposed at the second end. The first airfoil radially extends from the first outer shroud.
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公开(公告)号：US20190017398A1
公开(公告)日：2019-01-17
申请号：US15647500
申请日：2017-07-12
Applicant: United Technologies Corporation
Inventor： William R. Edwards , Nicholas Hunnewell
Abstract: A stator vane assembly for a gas turbine engine includes an inner vane support defining a first aperture, an outer vane support defining a second aperture, a stator having an inner end that extends through the first aperture and an outer end that extends through the second aperture, and a first bracket. The first bracket is operatively connected to the inner vane support and extends over the first aperture. The first bracket and the inner vane support defining a first pocket.
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