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11.发明授权公开(公告)号：US10830448B2
公开(公告)日：2020-11-10
申请号：US15334776
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Monica Pacheco-Tougas , Kevin Zacchera , Jonathan Jeffery Eastwood
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.
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公开(公告)号：US10808928B2
公开(公告)日：2020-10-20
申请号：US14912175
申请日：2014-08-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.
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公开(公告)号：US10088159B2
公开(公告)日：2018-10-02
申请号：US14773990
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Nurhak Erbas-Sen , James B. Hoke , John S. Tu , Monica Pacheco-Tougas
Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.
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公开(公告)号：US10077903B2
公开(公告)日：2018-09-18
申请号：US14886973
申请日：2015-10-19
Applicant: United Technologies Corporation
Inventor： John S. Tu , James B. Hoke , Monica Pacheco-Tougas , Timothy S. Snyder , Dennis M. Moura , Anthony Van
CPC classification number: F23R3/06 , F23R3/002 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.
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15.发明申请公开(公告)号：US20180112878A1
公开(公告)日：2018-04-26
申请号：US15334776
申请日：2016-10-26
Applicant: United Technologies Corporation
Inventor： Monica Pacheco-Tougas , Kevin Zacchera , Jonathan Jeffery Eastwood
Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.
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Patent Agency Ranking
16.发明申请公开(公告)号：US20160265773A1
公开(公告)日：2016-09-15
申请号：US15032119
申请日：2014-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dennis M. Moura , Monica Pacheco-Tougas , Jonathan J. Eastwood , Lee E. Bouldin
CPC classification number: F23R3/002 , F02C7/18 , F02C7/24 , F05D2220/32 , F05D2240/15 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/941 , F23M5/00 , F23M5/08 , F23M5/085 , F23R3/005 , F23R3/007 , F23R3/04 , F23R3/06 , F23R3/50 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
Abstract: A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.
Abstract translation: 提供了一种用于涡轮发动机的燃烧器，其包括燃烧器壁。 燃烧器壁包括外壳和隔热罩，其附接到外壳。 在外壳和隔热罩之间限定一个或多个冷却空腔，并将限定在外壳中的多个孔与限定在隔热罩中的多个孔流体耦合。 隔热罩中的孔包括第一孔和第二孔。 第一孔和隔热罩的表面之间的入射角与第二孔和表面之间的入射角不同。
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公开(公告)号：US20160238250A1
公开(公告)日：2016-08-18
申请号：US15029517
申请日：2014-10-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dennis M. Moura , Jonathan J. Eastwood , Lee E. Bouldin , Monica Pacheco-Tougas
Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
Abstract translation: 用于涡轮发动机的组件包括燃烧器壁。 燃烧器壁包括壳体，隔热罩和环形平台。 隔热罩安装在外壳上。 地面在壳体和隔热罩之间垂直延伸。 地面在陆地外表面和内表面之间横向延伸，其至少部分地限定了燃烧器壁中的骤冷孔。 陆面外表面和内表面之间的横向距离围绕淬火孔径变化。
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18.发明申请ACTIVE COOLING OF GROMMET BOSSES FOR A COMBUSTOR PANEL OF A GAS TURBINE ENGINE 审中-公开气体涡轮发动机燃烧器面板的主动冷却公开(公告)号：US20160025342A1
公开(公告)日：2016-01-28
申请号：US14773990
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nurhak Erbas-Sen , James B. Hoke , John S. Tu , Monica Pacheco-Tougas
CPC classification number: F23R3/002 , F02C7/18 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.
Abstract translation: 根据本公开的一个公开的非限制性实施例的用于燃气涡轮发动机的燃烧器的衬套组件包括具有多个索环冷却通道的索环。
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公开(公告)号：US11287132B2
公开(公告)日：2022-03-29
申请号：US16799083
申请日：2020-02-24
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Jonathan J. Eastwood , Lee E. Bouldin , Monica Pacheco-Tougas
Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
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公开(公告)号：US10690348B2
公开(公告)日：2020-06-23
申请号：US15032080
申请日：2014-11-04
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Monica Pacheco-Tougas , Jonathan J. Eastwood , Lee E. Bouldin
Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
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