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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：US11047397B2
公开(公告)日：2021-06-29
申请号：US15110889
申请日：2014-12-26
Applicant: United Technologies Corporation
Inventor： Richard K. Hayford , Robert J. Morris , Charles H. Warner , Charles P. Gendrich
Abstract: A gas turbine engine includes a circumferential array of stator vanes that have first and second vanes with different vibrational frequencies than one another. The first vanes are arranged in circumferentially alternating relationship with the second vanes.
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公开(公告)号：US20150292342A1
公开(公告)日：2015-10-15
申请号：US14644596
申请日：2015-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark David Ring , Scot A. Webb , Mark J. Rogers , Gerald D. Cassella , Charles H. Warner , Eric A. Kuehne , Jonathan J. Earl , Matthew M. Zietala , Neil L. Tatman , Randall J. Butcher , Matthew R. Willett , Nicholas R. Leslie
CPC classification number: F01D9/041 , F01D9/042 , F01D25/246 , F05D2220/32 , F05D2230/61 , F05D2240/12 , F05D2240/80 , Y02T50/672
Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to said second end-of-cluster vane; and a multiple of base vanes between said first end-of-cluster vane and said neighbor vane.
Abstract translation: 用于燃气涡轮发动机的叶片组包括第一端簇叶片，第二端簇叶片，与所述第二端簇叶片相邻的相邻叶片; 以及在所述第一端部叶片叶片和所述相邻叶片之间的多个基部叶片。
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公开(公告)号：US11125092B2
公开(公告)日：2021-09-21
申请号：US16103462
申请日：2018-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffrey D. Ponchak , Alex Daniel Morrow , Charles H. Warner
Abstract: A gas turbine engine includes a case assembly and a stator segment. The case assembly defines a first slot having a first surface and a second surface. The stator segment includes a shroud body axially extends between a first body end and a second body end. A first flange extends into the first slot. The first flange has a first flange first side, a first flange second side, a first flange first surface and a first flange second surface each circumferentially extending between the first flange first side and the first flange second side. A first portion of the first flange first surface engages the first surface. A second portion of the first flange first surface. A third portion of the first flange first surface is spaced apart from the first surface.
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公开(公告)号：US10677266B1
公开(公告)日：2020-06-09
申请号：US15869939
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 0.63-0.73 inch (16.0-18.5 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 0.61-0.71 inch (15.5-18.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4852±10% Hz, a second mode with a frequency of 11917±10% Hz, a third mode with a frequency of 30842±10% Hz and a fourth mode with a frequency of 35225±10% Hz.
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Patent Agency Ranking
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：US20150300205A1
公开(公告)日：2015-10-22
申请号：US14665780
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Matthew R. Willett , Charles H. Warner , Gerald D. Cassella , Jonathan J. Earl , Christopher B. Lyons
CPC classification number: F01D25/246 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/30 , F05D2230/60 , F05D2240/12 , F05D2240/14 , F05D2240/80
Abstract: Systems and methods are disclosed for anti-rotation lugs. A stator for a gas turbine engine may comprise an outer shroud, an inner shroud, and a plurality of vanes located between the outer shroud and the inner shroud. A plurality of anti-rotation lugs may be coupled to the inner shroud. The anti-rotation lugs may be configured to contact a diffuser case in order to prevent rotation of the stator. The anti-rotation lugs may comprise a body and a tapered shoulder. The tapered shoulder may distribute stress concentrations in the anti-rotation lugs.
Abstract translation: 公开了用于防旋转凸耳的系统和方法。 用于燃气涡轮发动机的定子可以包括外护罩，内护罩和位于外护罩和内护罩之间的多个叶片。 多个防旋转凸耳可以联接到内护罩。 防旋转凸耳可以被配置为接触扩散器壳体以防止定子旋转。 防旋转凸耳可以包括主体和锥形肩部。 锥形肩部可以在抗旋转凸耳中分布应力集中。
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公开(公告)号：US11767763B1
公开(公告)日：2023-09-26
申请号：US15869372
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , Carl S. Richardson , Ling Liu , Robert W. Fessenden
CPC classification number: F01D5/16 , F01D5/005 , F01D5/34 , F01D9/041 , F02C3/06 , F05D2220/3219 , F05D2220/323 , F05D2240/12 , F05D2240/24 , F05D2240/30 , F05D2260/96 , F05D2300/175 , F05D2300/522
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 1.01-1.15 inch (25.7-29.3 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 0.54-0.66 inch (13.6-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2033 ± 15% Hz, a second mode with a frequency of 7023 ± 15% Hz, a third mode with a frequency of 12082 ± 15% Hz and a fourth mode with a frequency of 19769 ± 15% Hz.
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