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

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/06 ,  F02C7/18

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

IPC: F23R3/06 ,  F23R3/04 ,  F02C7/18 ,  F23R3/00

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

IPC: F23R3/00 ,  F23R3/06 ,  F23R3/50 ,  F23M5/00 ,  F23M5/08 ,  F02C7/18 ,  F02C7/24 ,  F23R3/04

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：US20180073737A1

公开(公告)日：2018-03-15

申请号：US15266036

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott A. Elliott ,  Robert M. Sonntag ,  John S. Tu ,  Anthony Van ,  Joseph J. Sedor ,  Robert selinsky, JR. ,  John J. Rup, JR. ,  Neil B. Ridgeway ,  Gerard V. Cadieux ,  Jeffrey Leon ,  Monica Pacheco-Tougas ,  Lisa A. Jenkins ,  Lisa Tse ,  Andrew Cervoni ,  Frank J. Trzcinski

IPC: F23R3/00 ,  F23R3/44 ,  F02C7/12

CPC classification number: F23R3/002 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2300/611 ,  F23R3/06 ,  F23R3/44 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03045

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

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

IPC: F23R3/06 ,  F23R3/60 ,  F23R3/00

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。

公开(公告)号：US20160334103A1

公开(公告)日：2016-11-17

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

IPC: F23R3/06 ,  F23R3/60 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03041 ,  Y02T50/675

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.

Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器中的衬板。 衬板包括具有唇缘和第一密封凸台的主要稀释通道。 衬里面板还包括具有邻近第一密封凸台的第二密封凸台的次要稀释通道。

公开(公告)号：US20160201913A1

公开(公告)日：2016-07-14

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

IPC: F23R3/06 ,  F23R3/00

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.

Abstract translation: 本公开的方面涉及一种用于包含在飞行器的衬套中的冷却设计特征，包括：多个成角度的孔，以及分开任何两个成角度孔的所有组合的至少一个通孔，其中所述至少一个 通孔以基本上垂直于衬套的表面的角度定向，并且其中多个成角度孔中的每一个不平行于至少一个通孔。

公开(公告)号：US20160131365A1

公开(公告)日：2016-05-12

申请号：US14935076

申请日：2015-11-06

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Alexander W. Williams

IPC: F23R3/16 ,  B64D27/10 ,  F02C7/18

Abstract: Aspects of the disclosure are directed to a liner associated with an engine of an aircraft. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.

Abstract translation: 本公开的方面涉及与飞行器的发动机相关联的衬管。 该衬套包括一个面板和一组凸起，其被构造成增强面板的冷却并且分布在对应于面板的冷侧的面板的第一侧的至少一部分上。