公开(公告)号：US11248490B2

公开(公告)日：2022-02-15

申请号：US16004687

申请日：2018-06-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan K. Galle ,  Brian C. McLaughlin

IPC: F01D25/12 ,  F02C7/12

Abstract: A thermally responsive flow meter may comprise a coil and a plate coupled to the coil. The plate may define a first airflow aperture. The plate may translate in a circumferential direction in response to a thermal expansion of the coil. The thermally responsive flow meter may regulate the flow of air through a second airflow aperture.

公开(公告)号：US10436071B2

公开(公告)日：2019-10-08

申请号：US15099755

申请日：2016-04-15

Applicant: United Technologies Corporation

Inventor： Daniel S. Rogers ,  Jeremy Drake ,  Brian C. McLaughlin

IPC: F01D25/28 ,  F01D11/08 ,  F01D25/24

Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.

公开(公告)号：US10408074B2

公开(公告)日：2019-09-10

申请号：US15137395

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Brian C. McLaughlin ,  Thomas E. Clark ,  Peter J. Milligan ,  Dairus Deylan McDowell ,  Jaimie Schweitzer ,  Jeremy Drake ,  Richard K. Hayford

IPC: F01D11/00 ,  F16J15/02 ,  F02C7/28 ,  F02C7/20 ,  F01D25/24 ,  F16J15/08

Abstract: Aspects of the disclosure are directed to a seal comprising: a first leg that emanates from a center point of the seal and is configured to contact a first component, a second leg that emanates from the center point and is configured to contact a second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius, and a third leg that emanates from the center point.

公开(公告)号：US10995626B2

公开(公告)日：2021-05-04

申请号：US16355003

申请日：2019-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian C. McLaughlin ,  Terence P. Tyler

IPC: F01D11/08 ,  F01D25/24

Abstract: A blade outer air seal segment may comprise a radially outward surface and a radially inward surface oriented away from the radially outward surface. A cooling channel may be located between the radially outward surface and the radially inward surface. An inlet orifice may be fluidly coupled to the cooling channel. A stress-relief orifice may be between the inlet orifice and the cooling channel.

公开(公告)号：US10563542B2

公开(公告)日：2020-02-18

申请号：US15161716

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Brian C. McLaughlin

IPC: F01D25/28 ,  F01D25/24 ,  F23R3/60 ,  F01D5/02 ,  F02C3/04 ,  F02C3/14 ,  F01D9/02

Abstract: A retention device includes a retention block including an opening extending through the retention block in a first direction. A tab also extends from the retention block in the first direction. A fastener extends through the opening and includes a head configured to engage the retention block. A clinch nut is coupled to the fastener with an interface surface of the clinch nut configured to engage the tab of the retention block.

公开(公告)号：US20180073380A1

公开(公告)日：2018-03-15

申请号：US15260701

申请日：2016-09-09

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Brian C. McLaughlin

IPC: F01D11/12 ,  F01D25/28

CPC classification number: F01D11/12 ,  F01D11/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/60

Abstract: A fluid flow assembly may include an orifice plate having a set of orifices and a plenum defined by a blade outer air seal. The set of orifices may be aligned with and in fluid communication with the plenum. A gas turbine engine may include a vane outer support having an orifice plate, wherein the orifice plate includes a plurality of sets of orifices. The gas turbine engine may also include a blade outer air seal defining a plurality of plenums. Each set of orifices of the plurality of sets of orifices may be forward relative to and substantially axially aligned with a respective plenum of the plurality of plenums.

公开(公告)号：US11028712B2

公开(公告)日：2021-06-08

申请号：US16366860

申请日：2019-03-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Terence P. Tyler ,  Brian C. McLaughlin

IPC: F01D11/00 ,  F01D11/08

Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal. The second seal may include a seal support extending radially therefrom which mechanically supports the first seal during engine operation.

公开(公告)号：US10961862B2

公开(公告)日：2021-03-30

申请号：US16434779

申请日：2019-06-07

Applicant: United Technologies Corporation

Inventor： Paul M. Lutjen ,  Michael J. Bruskotter ,  Brian C. McLaughlin ,  Terence P. Tyler

IPC: F01D11/08 ,  F01D25/12

Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss.

公开(公告)号：US20170298776A1

公开(公告)日：2017-10-19

申请号：US15099755

申请日：2016-04-15

Applicant: United Technologies Corporation

Inventor： Daniel S. Rogers ,  Jeremy Drake ,  Brian C. McLaughlin

IPC: F01D25/28 ,  F01D11/08 ,  F01D25/24

CPC classification number: F01D25/28 ,  F01D11/08 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/64 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/11 ,  F05D2260/30

Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.

公开(公告)号：US20200291806A1

公开(公告)日：2020-09-17

申请号：US16355003

申请日：2019-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian C. McLaughlin ,  Terence P. Tyler

IPC: F01D11/08

Abstract: A blade outer air seal segment may comprise a radially outward surface and a radially inward surface oriented away from the radially outward surface. A cooling channel may be located between the radially outward surface and the radially inward surface. An inlet orifice may be fluidly coupled to the cooling channel. A stress-relief orifice may be between the inlet orifice and the cooling channel.