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公开(公告)号：US20150184857A1
公开(公告)日：2015-07-02
申请号：US14644227
申请日：2015-03-11
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Timothy S. Snyder
IPC: F23R3/26
CPC classification number: F23R3/002 , F02C7/12 , F23R3/04 , F23R3/06 , F23R3/12 , F23R3/14 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机的燃烧器部件尤其包括隔热板。 隔热板限定了在隔热板的厚度内的弯曲和微电路流动路径。 微电路流路包括入口径向向外的入口和出口。 弯曲处的微电路流动路径径向位于入口和出口之间，并且微电路流动路径跟随弯曲。 还公开了一种冷却燃气涡轮发动机的燃烧器的方法。
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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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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：US20200240638A1
公开(公告)日：2020-07-30
申请号：US16827195
申请日：2020-03-23
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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公开(公告)号：US10451281B2
公开(公告)日：2019-10-22
申请号：US14932556
申请日：2015-11-04
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a first layer vertically connected with a second layer. A first portion of the first layer overlaps and is vertically spaced from the second layer by a cavity. A second portion of the first layer is substantially vertically inline with an adjacent portion of the second layer. The second portion of the first layer at least partially forms a quench aperture vertically through the combustor wall.
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Patent Agency Ranking
公开(公告)号：US20190128522A1
公开(公告)日：2019-05-02
申请号：US16167873
申请日：2018-10-23
Applicant: United Technologies Corporation
Inventor： Stanislav Kostka , Frank J. Cunha
Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
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公开(公告)号：US20170159936A1
公开(公告)日：2017-06-08
申请号：US15039108
申请日：2014-12-31
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka
CPC classification number: F23R3/002 , F01D5/187 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/15 , F05D2240/35 , F05D2260/20 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/00017 , F23R2900/03041 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
Abstract: A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.
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公开(公告)号：US20160377289A1
公开(公告)日：2016-12-29
申请号：US15038774
申请日：2014-12-03
Applicant: United Technologies Corporation
Inventor： Stanislav Kostka, JR. , Frank J. Cunha
CPC classification number: F23R3/005 , F05D2240/35 , F23R3/002 , F23R3/04 , F23R3/06 , F23R3/50 , F23R2900/00017 , F23R2900/03042 , F23R2900/03044
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. 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 defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.
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壳体，隔热罩和环形体。 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。 环形体限定了流体耦合在冷却腔和淬火孔之间的第一冷却孔。 冷却腔位于外壳和隔热罩之间。
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19.发明申请公开(公告)号：US20160230996A1
公开(公告)日：2016-08-11
申请号：US15025631
申请日：2014-09-30
Applicant: United Technologies Corporation
Inventor： Stanislav Kostka , Frank J. Cunha
IPC: F23R3/00
CPC classification number: F23R3/002 , F23M5/00 , F23M5/04 , F23M5/085 , F23R3/005 , F23R3/007 , F23R3/06 , F23R3/08 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , F23R2900/03045
Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
Abstract translation: 为涡轮发动机提供燃烧器壁。 燃烧器壁包括燃烧器外壳和附接到外壳的燃烧器隔热罩。 隔热罩包括第一面板和第二面板，其在重叠接头中密封地接合第一面板。 冷却腔在外壳和隔热罩之间延伸，并且将外壳中的多个孔流体耦合在隔热罩中的多个孔。
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公开(公告)号：US09322560B2
公开(公告)日：2016-04-26
申请号：US13630888
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nurhak Erbas-Sen , Frank J. Cunha
CPC classification number: F23R3/50 , F23R3/002 , F23R3/04 , F23R3/10 , F23R3/16 , F23R3/283 , F23R2900/03041 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
Abstract: A heat shield is disclosed. The heat shield may comprise a body having a back surface and an opposite front surface, wherein an opening in the body communicates through the front and back surfaces. The heat shield may further comprise at least one radial rail disposed on the back surface and extending radially outward from the opening for directing cooling air flow.
Abstract translation: 公开了一种隔热罩。 隔热罩可以包括具有后表面和相对的前表面的主体，其中主体中的开口通过前表面和后表面连通。 隔热罩还可以包括设置在后表面上并从开口径向向外延伸以引导冷却气流的至少一个径向轨道。
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