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公开(公告)号：US10317078B2
公开(公告)日：2019-06-11
申请号：US15034702
申请日：2014-11-21
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka, Jr.
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defines a cooling aperture configured to direct air out of the cooling cavity to impinge against the body.
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公开(公告)号：US10386066B2
公开(公告)日：2019-08-20
申请号：US15032190
申请日：2014-11-21
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka, Jr.
Abstract: A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.
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公开(公告)号：US20160305325A1
公开(公告)日：2016-10-20
申请号：US15100363
申请日：2014-12-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frank J. Cunha , Stanislav Kostka, Jr.
CPC classification number: F02C7/18 , F02C7/264 , F02C7/266 , F05D2260/20 , F23R3/005 , F23R3/06 , F23R3/50 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.
Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁。 燃烧器壁包括壳体，隔热罩和环形体。 主体在内表面和外表面之间横向延伸。 内表面在燃烧器壁中限定了点火器孔。 外表面垂直在隔热罩和外壳之间。 壳体限定第一冷却孔，空气通过该第一冷却孔被引导以撞击外表面。
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公开(公告)号：US20160290643A1
公开(公告)日：2016-10-06
申请号：US15035356
申请日：2014-12-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frank J. Cunha , Stanislav Kostka, Jr.
CPC classification number: F23R3/002 , F02C7/12 , F02C7/18 , F02C7/24 , F02K1/822 , F05D2220/30 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/231 , F23R3/04 , F23R3/06 , F23R2900/03044 , Y02T50/675
Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.
Abstract translation: 提供了一种用于涡轮发动机的组件。 涡轮发动机组件的燃烧器壁包括外壳，隔热罩和与外壳和隔热罩接合的环形体。 环形体延伸穿过燃烧器壁。 环形体至少部分地沿着穿过燃烧器壁的中心线限定了淬火孔。 环形体还至少部分地限定与淬火孔径流体连通的冷却孔。 冷却孔的至少一部分相对于中心线从淬火孔径向向外延伸。
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公开(公告)号：US10794595B2
公开(公告)日：2020-10-06
申请号：US15113536
申请日：2015-02-03
Applicant: United Technologies Corporation
Inventor： Randal G. McKinney , Frank J. Cunha , Stanislav Kostka, Jr.
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.
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Patent Agency Ranking
公开(公告)号：US10753608B2
公开(公告)日：2020-08-25
申请号：US15034717
申请日：2014-11-21
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka, Jr.
Abstract: A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.
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公开(公告)号：US10480787B2
公开(公告)日：2019-11-19
申请号：US14669206
申请日：2015-03-26
Applicant: United Technologies Corporation
Inventor： Hoyt Y. Chang , Christos Adamopoulos , Stanislav Kostka, Jr.
Abstract: A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.
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公开(公告)号：US11112115B2
公开(公告)日：2021-09-07
申请号：US14910827
申请日：2014-06-30
Applicant: United Technologies Corporation
Inventor： Stanislav Kostka, Jr. , Randal G. McKinney , James B. Hoke , Timothy S. Snyder , Frank J. Cunha
Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.
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公开(公告)号：US10697636B2
公开(公告)日：2020-06-30
申请号：US15100374
申请日：2014-12-04
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka, Jr. , Randal G. McKinney
Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.
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公开(公告)号：US10598379B2
公开(公告)日：2020-03-24
申请号：US15034689
申请日：2014-11-25
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka, Jr.
Abstract: An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.
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