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

Inventor： Lee Edward Bouldin ,  Monica Pacheco-Tougas ,  Dennis M. Moura ,  Jonathan Jeffery Eastwood

IPC: F23R3/06 ,  F23M5/08 ,  F23R3/60 ,  F23R3/00

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.

公开(公告)号：US10605169B2

公开(公告)日：2020-03-31

申请号：US15490189

申请日：2017-04-18

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  James B. Hoke ,  Reza Rezvani

IPC: F02C7/12 ,  F23R3/00 ,  F23R3/16 ,  F23R3/06

Abstract: Combustor panels for use in gas turbine engine combustors having a panel body having a peripheral rail around a periphery of the panel body, a first boss formed on the panel body and surrounding a first aperture that passes through the panel body, and a first webbing that extends from the peripheral rail toward the first boss. A first annular channel is formed between the first webbing and the first boss and surrounds the first boss and a first web pocket is formed within the first webbing between the peripheral rail and the first boss and defines a local extension of the first annular channel extending from the first boss to the peripheral rail.

公开(公告)号：US20200025083A1

公开(公告)日：2020-01-23

申请号：US16241187

申请日：2019-01-07

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F02C7/18 ,  F23R3/16 ,  F23R3/26

Abstract: According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; and a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of the first component.

公开(公告)号：US20190219268A1

公开(公告)日：2019-07-18

申请号：US16239911

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/08 ,  F23R3/04

CPC classification number: F23R3/007 ,  F01D5/189 ,  F23R2900/03044

Abstract: A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.

公开(公告)号：US20180283687A1

公开(公告)日：2018-10-04

申请号：US15476431

申请日：2017-03-31

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Atul Kohli ,  Dustin W. Davis ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  Brandon W. Spangler ,  Trevor Rudy ,  Benjamin Bellows ,  Dave J. Hyland ,  James B. Hoke ,  Stephen K. Kramer ,  Dennis M. Moura

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F16B43/00 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

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

IPC: F23R3/00 ,  F23R3/06

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.

公开(公告)号：US20180187982A1

公开(公告)日：2018-07-05

申请号：US15905120

申请日：2018-02-26

Applicant: United Technologies Corporation

Inventor： Joe Ott ,  John J. Rup, JR. ,  Stanley J. Funk ,  Dennis M. Moura ,  Lexia Kironn ,  Roger O. Coffey

IPC: F28F1/00 ,  F23R3/28 ,  F16L9/18 ,  F16L59/14

CPC classification number: F28F1/00 ,  F16L9/18 ,  F16L59/14 ,  F23D2211/00 ,  F23D2900/00016 ,  F23R3/283

Abstract: A tube assembly that may be for a fuel nozzle of a fuel system of a gas turbine engine may have a first tube defining a first flowpath along a centerline, a second tube generally spaced radially outward from the first tube with a first void located between and defined by the first and second tubes, and a support structure located in the first void and extending between the first and second tubes. The support structure is constructed and arranged to minimize or eliminate thermal conduction between the tubes. The entire assembly may be additive manufactured as one unitary piece. One example of a method of operation may include designed-for breakage of the structural support due to thermal stresses thereby further minimizing thermal conduction between tubes.

公开(公告)号：US20180112597A1

公开(公告)日：2018-04-26

申请号：US15334804

申请日：2016-10-26

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Dennis M. Moura

IPC: F02C7/18 ,  F02C7/28 ,  F01D9/04

Abstract: A combustor seal for use in a combustor of a gas turbine engine including a seal with a multiple of slots that correspond with a multiple of 1st HPT vanes. A method of cooling within a gas turbine engine including communicating cooling air through combustor seal toward each of a multiple of 1st HPT vanes.

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

IPC: F23R3/00 ,  F02C7/18 ,  F02C7/24 ,  F23R3/04

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

IPC: F23R3/00 ,  F23R3/06

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。