-
公开(公告)号：US20200292172A1
公开(公告)日：2020-09-17
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.
-
公开(公告)号：US10731858B2
公开(公告)日：2020-08-04
申请号：US14913795
申请日：2014-09-16
Applicant: United Technologies Corporation
Inventor： Lee E. Bouldin , Jonathan J. Eastwood , Dennis M. Moura , Monica Pacheco-Tougas
Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.
-
公开(公告)号：US20160238253A1
公开(公告)日：2016-08-18
申请号：US15027082
申请日：2014-10-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dennis M. Moura , Jonathan J. Eastwood , Lee E. Bouldin
IPC: F23R3/06
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.
Abstract translation: 为燃气涡轮发动机的燃烧器部分的壁组件提供环形垫圈。 环形垫圈包括至少部分地限定腔室的壁。 燃气涡轮发动机内的壁组件包括具有热侧和冷侧的衬板。 壁组件还包括具有通道壁和横向于通道壁的凸缘壁的环形垫圈。 环形索环包括其中的室。 一种冷却燃气涡轮发动机内的壁组件的方法包括将空气喷射通过环形垫圈中的室。
-
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.
-
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.
-
Patent Agency Ranking
16.发明授权公开(公告)号：US10648666B2
公开(公告)日：2020-05-12
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 α 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 α 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.
-
公开(公告)号：US10571125B2
公开(公告)日：2020-02-25
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.
-
公开(公告)号：US10215410B2
公开(公告)日：2019-02-26
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
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.
-
公开(公告)号：US20180230856A1
公开(公告)日：2018-08-16
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.
-
20.发明申请CONTROLLED VARIATION OF PRESSURE DROP THROUGH EFFUSION COOLING IN A DOUBLE WALLED COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开气动涡轮发动机双层瓦楞机中的压力冷却控制压力变化公开(公告)号：US20160356500A1
公开(公告)日：2016-12-08
申请号：US14913795
申请日：2014-09-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee E. Bouldin , Jonathan J. Eastwood , Dennis M. Moura , Monica Pacheco-Tougas
Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.
Abstract translation: 燃气涡轮发动机的燃烧器包括多个安装到支撑壳体的衬板，所述多个衬板中的至少一个衬垫板包括在第一压力下操作的第一冲击腔和在第二压力下操作的第二冲击腔 不同于第一压力。 在燃气涡轮发动机的燃烧器内冷却壁组件的方法包括将空气引导通过支撑壳体和限定第一冲击腔和第二冲击腔的衬板。 第一冲击腔在第一压力下操作，第二冲击腔以不同于第一压力的第二压力运行。
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.011 seconds)
