公开(公告)号：US20200149432A1

公开(公告)日：2020-05-14

申请号：US16734965

申请日：2020-01-06

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Brian C. McLaughlin

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

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：US20200080437A1

公开(公告)日：2020-03-12

申请号：US16124480

申请日：2018-09-07

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  William M. Barker

IPC: F01D11/08 ,  F01D25/24

Abstract: A gas turbine engine includes a turbine blade rotating about an axis of rotation defining an axial direction. A blade outer air seal is positioned radially outward of a radially outer tip of the turbine blade. The blade outer air seal has a forward support and an aft support. The forward support is supported on a forward hook from a blade outer air seal support. The aft support is supported on an aft hook from the blade outer air seal support. The blade outer air seal has a central web extending between the forward support and the aft support and radially outwardly of the turbine blade radially outer tip. A radially outer chamber is defined radially outwardly of the central web, and axially intermediate the forward support and the aft support. The radially outer chamber is divided into at least two separate subchambers maintained at two different pressures. A forward subchamber is at a higher pressure than an aft subchamber. A seal separator separates the forward and aft subchambers.

公开(公告)号：US20200072084A1

公开(公告)日：2020-03-05

申请号：US16122481

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F01D25/24 ,  F01D11/08 ,  F01D11/00

Abstract: A blade outer air seal assembly contains a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The support structure has a first support member that engages a first axial side of the blade outer air seal. A second support member engages a second axial side of the blade outer air seal. A retaining clip secures the blade outer air seal to the support structure. The retaining clip has a first leg and a second leg that extends in a generally radial direction. The first leg abuts the first axial side and the second leg abuts the first support member.

公开(公告)号：US20200040757A1

公开(公告)日：2020-02-06

申请号：US16055636

申请日：2018-08-06

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark ,  Daniel J. Whitney

IPC: F01D11/12 ,  F01D25/24 ,  F01D25/28 ,  F01D9/04

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks, and the forward and aft hooks are supported on forward and aft seal hooks of an attachment. The blade outer air seal is formed of a plurality of laminate layered with a central web formed of a plurality of laminate members including an inner reinforcement member. An outer overwrap wraps around the inner reinforcement member. A method is also disclosed.

公开(公告)号：US10415416B2

公开(公告)日：2019-09-17

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 ,  F01D11/24

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：US09957897B2

公开(公告)日：2018-05-01

申请号：US14662581

申请日：2015-03-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas E. Clark ,  Jeffrey Vincent Anastas

IPC: F02C1/00 ,  F02C7/22 ,  F01D5/08 ,  F01D9/06 ,  F02C7/18

CPC classification number: F02C7/22 ,  F01D5/081 ,  F01D9/06 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/10 ,  F05D2240/81 ,  F05D2260/30 ,  Y02T50/676

Abstract: A gimbal tube system for an onboard injector (OBI) includes a transfer tube having a first transfer tube end that can be mounted to an inner diameter of a stator platform and a second transfer tube end defining a transfer tube pivot connector. The system also includes a gimbal tube including a first gimbal tube end that defines a gimbal tube pivot connector that can movably mount to the transfer tube pivot connector such that the gimbal tube and the transfer tube can move relative to each other at a pivot joint defined between the transfer tube and the gimbal tube. The gimbal tube further includes a second gimbal tube end defining a nozzle that can be inserted into the OBI.

公开(公告)号：US20180017260A1

公开(公告)日：2018-01-18

申请号：US15210090

申请日：2016-07-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas E. Clark ,  Harvey C. Lee ,  Brian C. McLaughlin ,  Jonathan Lemoine

IPC: F23R3/60 ,  F23R3/00 ,  F01D25/24 ,  F02C7/20

CPC classification number: F23R3/60 ,  F01D25/243 ,  F02C7/20 ,  F05B2230/606 ,  F05D2220/32 ,  F05D2240/35 ,  F23R3/002 ,  F23R2900/00005

Abstract: A combustor assembly for a gas turbine engine comprises a vane support ring; an annular combustor extending around a central axis and being located radially inwards of the vane support ring, the annular combustor including an aft end, a forward end with at least one opening through which at least one fuel nozzle is received, and an annular outer shell and an annular inner shell that define an annular combustion chamber there between, the annular outer shell including a radially-outwardly extending flange including at least one scallop cut; and a stop member integrally formed with the vane support ring.

公开(公告)号：US20170350265A1

公开(公告)日：2017-12-07

申请号：US15170451

申请日：2016-06-01

Applicant: United Technologies Corporation

Inventor： Brian C. McLaughlin ,  Thomas E. Clark

IPC: F01D11/00 ,  F02C7/28 ,  F01D25/12 ,  F02C7/18

CPC classification number: F01D11/005 ,  F01D25/12 ,  F01D25/246 ,  F02C7/18 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/202 ,  Y02T50/676

Abstract: A seal ring includes a disk having a radially outer end and an orifice at a center forming a radially inner end, a plurality of holes extending through the disk, and a rail having an annular shape extending axially away from the disk at a position that is between the radially outer end and the plurality of holes extending through the disk with the rail being configured to direct the flow of fluid.

公开(公告)号：US20170306779A1

公开(公告)日：2017-10-26

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 ,  F02C7/20 ,  F02C7/28

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：US11761343B2

公开(公告)日：2023-09-19

申请号：US16352114

申请日：2019-03-13

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  William M. Barker

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2300/6033

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of seal segments arranged circumferentially about an axis and mounted in the support structure by a carrier. The carrier has first and second hooks that extend radially outward from a platform along an axial length of the carrier. The first and second hooks are in engagement with the support structure.