公开(公告)号：US11371703B2

公开(公告)日：2022-06-28

申请号：US16239911

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/08 ,  F23R3/00 ,  F01D5/18 ,  F01D25/32 ,  F23R3/04

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：US10738701B2

公开(公告)日：2020-08-11

申请号：US15690555

申请日：2017-08-30

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Shawn M. McMahon ,  Kevin Zacchera ,  Noah Wadsworth ,  Christopher Whitfield ,  Sean D. Bradshaw ,  Dennis M. Moura

IPC: F01D9/02 ,  F02C7/18 ,  F02C7/28 ,  F23R3/42 ,  F01D11/00

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.

公开(公告)号：US10690346B2

公开(公告)日：2020-06-23

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 ,  F23R3/60 ,  F23R3/06 ,  F16B43/00

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：US10669939B2

公开(公告)日：2020-06-02

申请号：US15334804

申请日：2016-10-26

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Dennis M. Moura

IPC: F02C7/18 ,  F01D11/00 ,  F01D25/12 ,  F23R3/00 ,  F01D9/02 ,  F01D9/04 ,  F02C7/28

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：US10480868B2

公开(公告)日：2019-11-19

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: F16L9/18 ,  F23R3/32 ,  F28F1/00 ,  F23R3/28 ,  F16L59/14

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：US20190218976A1

公开(公告)日：2019-07-18

申请号：US16241176

申请日：2019-01-07

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F02C7/30 ,  F01D25/32 ,  F02C7/18 ,  F23R3/06

CPC classification number: F01D25/12 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/607 ,  F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/00004 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: 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 wherein the first component includes a cooling hole extending from the second surface to the first surface through the first component; 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 in fluid communication with the cooling hole for cooling the second surface of the second component; and a deflector forming a passageway with the second surface of the first component, the passageway configured to direct airflow into the cooling channel 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：US20190195496A1

公开(公告)日：2019-06-27

申请号：US16226892

申请日：2018-12-20

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/00 ,  F23M5/08 ,  F23M5/04

CPC classification number: F23R3/002 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/607 ,  F23M5/04 ,  F23M5/08 ,  F23R3/60 ,  F23R2900/00004 ,  F23R2900/00017 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: 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; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component; and a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated.

公开(公告)号：US20190195495A1

公开(公告)日：2019-06-27

申请号：US16226874

申请日：2018-12-20

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/00 ,  F23M5/08

CPC classification number: F23R3/002 ,  F02C7/185 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/607 ,  F23M5/08 ,  F23R3/00 ,  F23R3/045 ,  F23R3/06 ,  F23R2900/00004 ,  F23R2900/03044

Abstract: A gas turbine engine component comprising: a first component having a receiving aperture extending; a second component having a first surface and a second surface; and a passageway portion including a first end, a second end opposite the first end, and an outer surface extending from the second end to the first end, the passageway portion extending from the second surface of the second component through the receiving aperture of the first component, wherein the outer surface of the passageway portion and the first component define a gap therebetween, the gap fluidly connecting airflow in an airflow path proximate the second surface of the first component to the cooling channel, wherein the gap is configured to direct the airflow along the outer surface and the outer surface is shaped to redirect the airflow in a lateral direction parallel to the second surface such that a lateral airflow is generated.

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

IPC: F23R3/00 ,  F23R3/02 ,  F23R3/04 ,  F23R3/06

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：US09915480B2

公开(公告)日：2018-03-13

申请号：US14789496

申请日：2015-07-01

Applicant: United Technologies Corporation

Inventor： Joe Ott ,  John J. Rup, Jr. ,  Stanley J. Funk ,  Dennis M. Moura ,  Lyutsia Dautova ,  Roger O. Coffey

IPC: F16L9/18 ,  F28F1/00 ,  F23R3/28 ,  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 then al stresses thereby further minimizing thermal conduction between tubes.