公开(公告)号：US10718519B2

公开(公告)日：2020-07-21

申请号：US15893324

申请日：2018-02-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D Porter ,  James Tilsley Auxier

IPC: F23R3/00 ,  F23R3/06 ,  F23R3/60 ,  F23R3/50

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side, a cold side and at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a radial extent, a circumferential extent that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape.

公开(公告)号：US10364688B2

公开(公告)日：2019-07-30

申请号：US15343965

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： Raymond S Hummel ,  Steven D Porter ,  Julian Partyka

IPC: F01D9/02 ,  G01M1/38 ,  F01D25/04 ,  G01M1/32 ,  F01D5/02 ,  F01D5/30 ,  F04D29/66 ,  G01M1/36

Abstract: A minidisk for a rotor system may comprise a balance flange defining a hole array, which may include a first hole having a first width. The first hole may be configured to receive a balance weight. A second hole and a third hole may have a second width. The second hole and the third hole may be disposed adjacent to the first hole. The second width may be greater than the first width.

公开(公告)号：US11248791B2

公开(公告)日：2022-02-15

申请号：US15889764

申请日：2018-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D Porter ,  Jon E Sobanski

IPC: F23R3/06 ,  B22C7/02 ,  F01D25/12 ,  F23R3/00 ,  B22D25/02 ,  F23R3/50 ,  F02K1/82 ,  F02C7/24 ,  F02K3/06

Abstract: A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.

公开(公告)号：US10830435B2

公开(公告)日：2020-11-10

申请号：US15889816

申请日：2018-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jon E Sobanski ,  Steven D Porter

IPC: F23R3/00 ,  F02C7/24

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface, a rail member disposed on the cold side proximate a first portion of the outer perimeter, the rail member having an outer wall and an inner wall, and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having a cross sectional area that increases from the inner wall to the outer wall.

公开(公告)号：US10808936B2

公开(公告)日：2020-10-20

申请号：US16020736

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Steven D Porter ,  John T Ols ,  Fumitaka Ichihashi

IPC: F23R3/50 ,  F23R3/06 ,  F23R3/00

Abstract: A heat shield panel for a gas turbine engine combustor may comprise a perimetrical rail extending at least partially around a perimeter of the heat shield panel and defining a main backside cavity, a plurality of air admittance holes, each air admittance hole extending along a hole axis, and a midrail dividing the main backside cavity into a first backside cavity and a second backside cavity, wherein at least a portion of the midrail is axially offset from at least one of the hole axes.

公开(公告)号：US11022307B2

公开(公告)日：2021-06-01

申请号：US15902171

申请日：2018-02-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jon E Sobanski ,  Steven D Porter

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/18 ,  F23R3/50

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

公开(公告)号：US11009230B2

公开(公告)日：2021-05-18

申请号：US15889793

申请日：2018-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D Porter ,  Jon E Sobanski

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/50

Abstract: A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface, a rail member disposed on the cold side proximate a first portion of the outer perimeter, the rail member having an outer wall and an inner wall, an undercut portion within the second surface proximate the inner wall of the rail member and an orifice extending through the rail member, from the inner wall to the outer wall.

公开(公告)号：US20200003423A1

公开(公告)日：2020-01-02

申请号：US16020736

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Steven D Porter ,  John T Ols ,  Fumitaka Ichihashi

IPC: F23R3/50 ,  F23R3/06

Abstract: A heat shield panel for a gas turbine engine combustor may comprise a perimetrical rail extending at least partially around a perimeter of the heat shield panel and defining a main backside cavity, a plurality of air admittance holes, each air admittance hole extending along a hole axis, and a midrail dividing the main backside cavity into a first backside cavity and a second backside cavity, wherein at least a portion of the midrail is axially offset from at least one of the hole axes.

公开(公告)号：US20190242579A1

公开(公告)日：2019-08-08

申请号：US15889764

申请日：2018-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D Porter ,  Jon E Sobanski

IPC: F23R3/06 ,  F02K3/06

CPC classification number: F23R3/06 ,  B22C7/02 ,  B22D25/02 ,  F01D25/12 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/15 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.

公开(公告)号：US10107118B2

公开(公告)日：2018-10-23

申请号：US14900737

申请日：2014-06-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T Ols ,  Richard N Allen ,  Paul K Sanchez ,  Steven D Porter ,  Jonathan Lemoine

IPC: F01D11/02 ,  F01D9/04 ,  F01D5/08 ,  F01D11/00

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.