公开(公告)号：US10590523B2

公开(公告)日：2020-03-17

申请号：US15886333

申请日：2018-02-01

Applicant: United Technologies Corporation

Inventor： Charles R. Beaudoin ,  Christopher W. Strock

IPC: C23C4/067 ,  C23C4/134 ,  F01D11/12 ,  F16J15/44

Abstract: An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer. The abradable material is composed of aluminum powder forming a metal matrix, and co-deposited methyl methacrylate particles and/or hexagonal boron nitride particles embedded as filler in the metal matrix.

公开(公告)号：US20200049020A1

公开(公告)日：2020-02-13

申请号：US16658690

申请日：2019-10-21

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F01D5/28 ,  F04D29/38 ,  F01D25/24 ,  F01D5/14 ,  F01D11/12 ,  F04D29/32 ,  F04D29/02

Abstract: A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.

公开(公告)号：US10544698B2

公开(公告)日：2020-01-28

申请号：US15616545

申请日：2017-06-07

Applicant: United Technologies Corporation

Inventor： Pantcho Stoyanov ,  Christopher W. Strock ,  Agnieszka M. Wusatowska-Sarnek

IPC: F01D11/12 ,  F01D5/02 ,  F01D21/00 ,  F01D25/24

Abstract: An embodiment of a gas turbine engine component includes an abrasive coating disposed on at least a portion of a sealing region. The abrasive coating includes an inner abrasive region disposed outward of the sealing region in a coating thickness direction, and an outer abrasive region disposed outward of the inner abrasive region in the coating thickness direction. The inner abrasive region includes abrasive particles retained in an inner matrix, and the outer abrasive region includes abrasive particles retained in an outer matrix. At least one of the inner matrix and the outer matrix is modified with a first indicator material. At least one aspect of the first indicator material corresponds to a thickness range of the abrasive coating being within the inner thickness region or the outer thickness region.

公开(公告)号：US10526908B2

公开(公告)日：2020-01-07

申请号：US15496839

申请日：2017-04-25

Applicant: United Technologies Corporation

Inventor： Kevin Seymour ,  Christopher W. Strock

IPC: F01D11/12 ,  F01D5/02 ,  F04D29/32 ,  F04D29/08 ,  C23C4/134

Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.

公开(公告)号：US10472981B2

公开(公告)日：2019-11-12

申请号：US14769834

申请日：2014-01-30

Applicant: United Technologies Corporation

Inventor： John R. Farris ,  Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D11/24 ,  F01D5/14 ,  F01D9/02

Abstract: A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, a body having a first outer face meeting a second outer face at an intersection, the body having a plurality of apertures extending from an opening in the first outer face to an opening on the second outer face; and a coating filling at least a portion of the plurality of apertures.

公开(公告)号：US10472729B2

公开(公告)日：2019-11-12

申请号：US15988109

申请日：2018-05-24

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  James O. Hansen

IPC: C25D11/16 ,  F01D5/02 ,  F01D5/28 ,  F01D25/24 ,  C25D11/24 ,  C25D11/18 ,  F01D5/20 ,  C25D11/02

Abstract: A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions (158′; 402′) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).

公开(公告)号：US20190195080A1

公开(公告)日：2019-06-27

申请号：US16289784

申请日：2019-03-01

Applicant: United Technologies Corporation

Inventor： Jose R. Paulino ,  Christopher W. Strock

IPC: F01D11/08 ,  C23C4/02

CPC classification number: F01D11/08 ,  B33Y10/00 ,  B33Y80/00 ,  C23C4/02 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2300/502

Abstract: A gas turbine engine article includes a substrate that has at least one step, and the step includes an undercut. A thermally insulating topcoat is disposed on the substrate. The thermally insulating topcoat includes at least one fault that extends from the step.

公开(公告)号：US10301949B2

公开(公告)日：2019-05-28

申请号：US14761477

申请日：2013-01-29

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Changsheng Guo

IPC: C08K7/22 ,  C08K7/28 ,  C09D5/00 ,  F01D5/28 ,  C08G77/24 ,  C08L83/04 ,  C08L83/08 ,  F01D11/00 ,  F01D11/12 ,  C09D183/04

Abstract: One aspect of the disclosure involves a rub material comprising a polymeric matrix and polymer micro-balloon filler in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least 1.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the micro-balloons at least locally have a concentration of 5-50% by volume.

公开(公告)号：US10267174B2

公开(公告)日：2019-04-23

申请号：US15140903

申请日：2016-04-28

Applicant: United Technologies Corporation

Inventor： Xuan Liu ,  Christopher W. Strock ,  Russell A. Beers

IPC: F01D11/08 ,  F01D11/12 ,  F01D25/00 ,  F01D25/18 ,  C23C4/134 ,  C23C4/126 ,  C23C4/131 ,  C23C4/073 ,  C22C1/08 ,  C22C19/05 ,  F01D5/28 ,  C22C1/10

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, ≥35% nickel, 12.0-20.0% cobalt, 5.0-15.0% aluminum, and 5.0-15.0% chromium.

公开(公告)号：US20190078463A1

公开(公告)日：2019-03-14

申请号：US15700010

申请日：2017-09-08

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D25/00 ,  C23C4/134 ,  C23C4/04 ,  C09D1/00 ,  C09D5/28 ,  C01F7/02 ,  F02C3/00 ,  F01D5/28 ,  F01D5/34

Abstract: A method comprising: spraying a ceramic coating to a substrate to a thickness of at least 5.0 mils (127 micrometers) without quench; and after the spraying, directing a carbon dioxide flow to a surface of the coating.