公开(公告)号：US20160061330A1

公开(公告)日：2016-03-03

申请号：US14836302

申请日：2015-08-26

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis

IPC: F16J15/32 ,  B23K31/02

CPC classification number: F16J15/3288 ,  B23K31/02 ,  F01D11/005 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/56 ,  F05D2300/175 ,  F16J15/3268 ,  F16J15/328

Abstract: A dual-ended brush seal assembly that may be for turbine engine includes a first structure having a first surface and a second structure having a second surface. A brush seal of the assembly includes a bent bristle pack having a first end in sealing contact with the first surface and an opposite second end in sealing contact with the second surface. The first and second ends project in respective first and second directions that generally traverse one-another.

Abstract translation: 可用于涡轮发动机的双端刷式密封组件包括具有第一表面的第一结构和具有第二表面的第二结构。 组件的刷密封件包括弯曲的刷毛组，其具有与第一表面密封接触的第一端和与第二表面密封接触的相对的第二端。 第一和第二端在各自的第一和第二方向上突出，其通常彼此横越。

公开(公告)号：US20150226132A1

公开(公告)日：2015-08-13

申请号：US14611920

申请日：2015-02-02

Applicant: United Technologies Corporation

Inventor： Carson A. Roy Thill ,  Mark Broomer ,  Timothy M. Davis ,  Craig R. McGarrah ,  Mark J. Rogers ,  Russell E. Keene ,  Anthony B. Swift

IPC: F02C7/28 ,  F01D25/24 ,  F02C3/04

CPC classification number: F02C7/28 ,  F01D11/005 ,  F01D25/24 ,  F01D25/246 ,  F02C3/04 ,  F05D2240/56 ,  F05D2240/58 ,  F05D2260/30 ,  F16J15/0887

Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.

Abstract translation: 用于燃气涡轮发动机的密封组件包括发动机静止结构。 第一和第二构件将空腔彼此流体地分开。 密封组件由发动机结构捕获。 密封组件包括承载件和接合第一构件的密封件。 第二个成员由承运人捕获。

公开(公告)号：US11486497B2

公开(公告)日：2022-11-01

申请号：US15653892

申请日：2017-07-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Timothy M. Davis ,  Mark J. Rogers ,  Jeffrey M. Wittman ,  James R. Plante

IPC: F01D11/00 ,  F16J15/3288 ,  F16J15/3212

Abstract: A seal structure may comprise a cavity defined at least partially by an axial surface and a radial surface. A brush seal may be disposed in the cavity. The brush seal may comprise a bristle pack and a backing plate coupled to the bristle pack. A first surface of the backing plate may contact the axial surface, and a second surface of the backing plate may contact the radial surface.

公开(公告)号：US20190353044A1

公开(公告)日：2019-11-21

申请号：US16531571

申请日：2019-08-05

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Paul M. Lutjen

IPC: F01D11/00 ,  F16J15/10 ,  F16J15/06 ,  F16J15/08 ,  F16J15/34

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. A wave spring disposed between the first and second seal sections biases the first and second seal sections away from one another. A compliant seal is carried by the second seal section. Other combinations of seal sections, wave springs, and compliant seals are also disclosed.

公开(公告)号：US10451204B2

公开(公告)日：2019-10-22

申请号：US14765849

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Mark Broomer ,  Russell E. Keene ,  Timothy M. Davis ,  Mark J. Rogers

IPC: F16L23/02 ,  F01D11/00 ,  F01D25/24 ,  F16L23/16 ,  F16L25/00 ,  F01D11/12

Abstract: A turbine shroud for incorporation in a turbine of a gas turbine engine has a plurality of butted shroud segments circumferentially arrayed to form a ring. Each of the shroud segments has an arcuate main shroud body portion, a radially inward extending annular flange attached to a first end of the main body portion, and a radially outward extending flange with a plurality of mounting apertures attached to a second end of the main shroud body portion. A first mounting aperture is sized smaller than an adjacent second mounting aperture in the radially outward extending flange.

公开(公告)号：US10316685B2

公开(公告)日：2019-06-11

申请号：US15024686

申请日：2014-08-01

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Brian Duguay

IPC: F01D11/22

Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.

公开(公告)号：US10280778B2

公开(公告)日：2019-05-07

申请号：US14770678

申请日：2014-02-24

Applicant: United Technologies Corporation

Inventor： Mark J. Rogers ,  Timothy M. Davis ,  Mark Broomer ,  Kevin W. White ,  Craig McGarrah ,  Carson A. Roy Thill

IPC: F01D11/00 ,  F02C7/28 ,  F16J15/08 ,  F16J15/06 ,  F01D25/26

Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.

公开(公告)号：US10202863B2

公开(公告)日：2019-02-12

申请号：US15162069

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Mark F. Zelesky ,  Michael G. McCaffrey

IPC: F01D11/00 ,  F16J15/02 ,  F16J15/44 ,  F01D11/08

Abstract: An annular ring for sealing a flow includes an inner ring and a tab. The tab extends radially and is configured to restrict axial movement of the seal.

公开(公告)号：US10145308B2

公开(公告)日：2018-12-04

申请号：US14611920

申请日：2015-02-02

Applicant: United Technologies Corporation

Inventor： Carson A. Roy Thill ,  Mark Broomer ,  Timothy M. Davis ,  Craig R. McGarrah ,  Mark J. Rogers ,  Russell E. Keene ,  Anthony B. Swift

IPC: F02C7/28 ,  F01D11/00 ,  F01D25/24 ,  F02C3/04 ,  F16J15/08

Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.

公开(公告)号：US09970311B2

公开(公告)日：2018-05-15

申请号：US14198049

申请日：2014-03-05

Applicant: United Technologies Corporation

Inventor： Michael S. Stevens ,  Jeremy Drake ,  Brian Duguay ,  Timothy M. Davis ,  Ryan M. Kohn ,  Dairus D. McDowell ,  Brian McLaughlin

IPC: F01D25/28 ,  F01D11/12 ,  F01D25/00 ,  B23P15/00

CPC classification number: F01D11/12 ,  B23P15/008 ,  F01D25/00 ,  F01D25/285 ,  F05D2230/64 ,  F05D2300/43 ,  Y10T29/4932 ,  Y10T156/10

Abstract: A method of assembling a gas turbine engine is provided that includes locating a consumable assembly tool within the engine. The consumable assembly tool is attached to another component of the gas turbine engine. The engine is run to vaporize the consumable assembly tool.