-
公开(公告)号：US10240790B2
公开(公告)日：2019-03-26
申请号：US15031908
申请日：2014-10-31
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Dennis M. Moura
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell and a heat shield. The heat shield includes a base and a plurality of panel rails. The panel rails are connected to the base and extend vertically to the shell. The panel rails include first and second rails. A vertical height of the first rail at a first location is less than a vertical height of the second rail at a second location.
-
公开(公告)号：US10550725B2
公开(公告)日：2020-02-04
申请号：US15297459
申请日：2016-10-19
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Timothy Dale
Abstract: Aspects of the disclosure are directed to a system for an engine having an axial centerline, comprising: a diffuser case, a turbine case, and a turbine vane support, where the diffuser case and the turbine case are coupled to one another via a substantially radially oriented flange, where the turbine vane support includes a heat shield for the flange, and where the turbine vane support includes a radially outward projecting tab that couples to the turbine case via a radial interference fit.
-
公开(公告)号：US10208949B2
公开(公告)日：2019-02-19
申请号：US15096624
申请日：2016-04-12
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Jonathan M. Jause
Abstract: A swirler comprising an anti-rotation feature is provided. The swirler may be installed on a combustor within a gas turbine engine. The swirler may comprise a generally cylindrical profile. In this regard, the swirler may be configured to provide a generally uniform profile within the combustor. The swirler may comprise a floating collar with an anti-rotation feature. The swirler may also include a collar end plate that defines a slot that at least partially encloses the anti-rotation feature and minimizes rotational movement of the floating collar.
-
4.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。
-
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。
-
Patent Agency Ranking
公开(公告)号：US10684017B2
公开(公告)日：2020-06-16
申请号：US15027082
申请日：2014-10-21
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Jonathan J. Eastwood , Lee E. Bouldin
Abstract: An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.
-
公开(公告)号：US10655856B2
公开(公告)日：2020-05-19
申请号：US15105427
申请日：2014-12-19
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Dennis M. Moura , Lee E. Bouldin , Monica Pacheco-Tougas
Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.
-
公开(公告)号：US10100675B2
公开(公告)日：2018-10-16
申请号：US14958287
申请日：2015-12-03
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Dave J. Hyland , Timothy Dale
Abstract: An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly. The forward flange is configured to detachably engage a high pressure compressor and the aft flange is configured to detachably engage a high pressure turbine of the engine.
-
9.发明申请TURBINE ENGINE COMBUSTOR HEAT SHIELD WITH ONE OR MORE COOLING ELEMENTS 审中-公开涡轮发动机燃烧器带有一个或多个冷却元件的热风罩公开(公告)号：US20160258626A1
公开(公告)日：2016-09-08
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.
Abstract translation: 为涡轮发动机提供燃烧器壁。 燃烧室壁包括一个外壳和一个受到外壳侵蚀的隔热罩。 隔热罩包括一个导轨和一个连接到空腔中的导轨的冷却元件。 空腔在外壳和隔热罩之间沿垂直方向延伸。 空腔将壳体中的多个孔与隔热罩中的多个孔流体耦合。
-
10.发明申请ANGLED COMBUSTOR LINER COOLING HOLES THROUGH TRANSVERSE STRUCTURE WITHIN A GAS TURBINE ENGINE COMBUSTOR 审中-公开燃气轮机内燃机通过在涡轮发动机燃烧器中的横向结构冷却球公开(公告)号：US20160208704A1
公开(公告)日：2016-07-21
申请号：US14913770
申请日：2014-09-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee E. Bouldin , Dennis M. Moura , Jonathan J. Eastwood , Monica Pacheco-Tougas
Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.
Abstract translation: 用于燃气涡轮发动机的燃烧器的壁组件包括横向结构，其具有至少一个以其穿过的角度延伸的积液通道。 渗出通道包括在壁的外周的入口。 燃气涡轮发动机内的壁组件包括大致平行于支撑壳体的衬板和具有至少一个以一角度穿过其延伸的积液通道的横向结构。 渗出通道包括横向于衬垫板和支撑壳体的壁的外周中的入口。
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.016 seconds)
