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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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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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14.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：US20160084502A1
公开(公告)日：2016-03-24
申请号：US14853368
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka
CPC classification number: F23R3/04 , F01D9/02 , F01D9/065 , F02C6/06 , F02C7/04 , F02C9/16 , F04D29/44 , F05D2210/12 , F05D2210/13 , F05D2220/30 , F05D2240/35 , F23R3/005 , F23R3/02
Abstract: A diffuser assembly is provided for a turbine engine. This diffuser assembly includes a. diffuser module with a combustor plenum and a mixing chamber. The diffuser module is configured to receive first and second airflows into the mixing chamber and direct a mixed airflow out of the mixing chamber. The diffuser module includes a mixer configured to mix the first and the second airflows together within the mixing chamber to provide the mixed airflow.
Abstract translation: 为涡轮发动机提供扩散器组件。 该扩散器组件包括a。 扩散器模块，具有燃烧室增压室和混合室。 扩散器模块被配置为将第一和第二气流接收到混合室中并将混合气流引导出混合室。 扩散器模块包括混合器，该混合器构造成将混合室内的第一和第二气流混合在一起以提供混合气流。
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Patent Agency Ranking
公开(公告)号：US20150292741A1
公开(公告)日：2015-10-15
申请号：US14680649
申请日：2015-04-07
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka , Timothy S. Snyder
CPC classification number: F23R3/002 , F02C7/28 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/00012 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A wall assembly of a combustor for a turbine engine includes a shell and a liner and a sealing interface structure. A cooling cavity is defined between the shell and liner and the sealing interface structure functions to minimize leakage out of the cooling cavity. The sealing interface structure may have a sealing width that is equal to or greater than twice the thickness of the liner and/or may include a chamber located between longitudinal segments of the sealing interface structure that inhibits leakage.
Abstract translation: 用于涡轮发动机的燃烧器的壁组件包括壳体和衬套以及密封接口结构。 在壳体和衬套之间限定了一个冷却腔，并且密封接口结构用于使冷却腔中的泄漏最小化。 密封界面结构可以具有等于或大于衬套厚度的两倍的密封宽度和/或可以包括位于密封界面结构的纵向段之间的室，其阻止泄漏。
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公开(公告)号：US10935244B2
公开(公告)日：2021-03-02
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：US10378773B2
公开(公告)日：2019-08-13
申请号：US14853368
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka
IPC: F23R3/04 , F04D29/44 , F01D9/02 , F01D9/06 , F02C6/06 , F23R3/02 , F02C7/04 , F02C9/16 , F23R3/00
Abstract: A diffuser assembly is provided for a turbine engine. This diffuser assembly includes a diffuser module with a combustor plenum and a mixing chamber. The diffuser module is configured to receive first and second airflows into the mixing chamber and direct a mixed airflow out of the mixing chamber. The diffuser module includes a mixer configured to mix the first and the second airflows together within the mixing chamber to provide the mixed airflow.
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公开(公告)号：US09909761B2
公开(公告)日：2018-03-06
申请号：US14680649
申请日：2015-04-07
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka , Timothy S. Snyder
CPC classification number: F23R3/002 , F02C7/28 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/00012 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A wall assembly of a combustor for a turbine engine includes a shell and a liner and a sealing interface structure. A cooling cavity is defined between the shell and liner and the sealing interface structure functions to minimize leakage out of the cooling cavity. The sealing interface structure may have a sealing width that is equal to or greater than twice the thickness of the liner and/or may include a chamber located between longitudinal segments of the sealing interface structure that inhibits leakage.
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公开(公告)号：US20160169522A1
公开(公告)日：2016-06-16
申请号：US14939667
申请日：2015-11-12
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Stanislav Kostka
IPC: F23R3/28
Abstract: A fuel injector guide is provided for a turbine engine combustor. The fuel injector guide includes a tubular base, an annular flange, a plurality of ribs and a flow turbulator. The base extends along an axis between first and second ends. The flange extends radially out from the base at the second end. The ribs are disposed around the base and extend axially out from the flange towards the first end. The flow turbulator is disposed between an adjacent pair of the ribs.
Abstract translation: 为涡轮发动机燃烧器提供燃料喷射器引导件。 燃料喷射器引导件包括管状基座，环形凸缘，多个肋和流动紊流器。 底座沿着第一和第二端之间的轴线延伸。 凸缘在第二端从底座径向伸出。 肋围绕基部设置并且从凸缘朝向第一端轴向延伸。 流动紊流器设置在相邻的一对肋之间。
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