公开(公告)号：US10273822B2

公开(公告)日：2019-04-30

申请号：US15026482

申请日：2014-09-25

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Mark R. Jaworowski ,  Frank W. Mase

IPC: F01D5/12 ,  F01D9/02 ,  F01D25/24 ,  F01D11/12 ,  C23C4/06 ,  C23C4/18 ,  C23C4/129 ,  C23C4/134 ,  C22C21/02 ,  C23C4/04 ,  C23C22/02 ,  C23C24/04 ,  C23C26/00

Abstract: A corrosion resistant aluminum alloy abradable coating for use as a seal material consists of a porous base metal alloy layer containing corrosion inhibiting metal compounds dispersed throughout the porous base metal alloy layer. A method of forming a corrosion resistant aluminum alloy abradable coating consists of co-thermal spraying aluminum alloy powder plus polymer powder and particles containing corrosion inhibiting metal compounds.

公开(公告)号：US20190120075A1

公开(公告)日：2019-04-25

申请号：US16218949

申请日：2018-12-13

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F01D11/12 ,  B22F3/10 ,  F01D5/28

Abstract: A method of manufacturing a net shaped seal comprising depositing a first layer of powder material on a substrate; the powder material comprising an abradable feedstock material comprising matrix alloy clad filler particles, wherein the matrix alloy cladding includes Al, Cu, Ni, Co, Cr, Fe, Si and Y; guiding a heat source over the powder material layer; laser sintering the powder material, the matrix alloy clad filler particles sinter in the absence of the filler particles melting; depositing a second layer of powder material over the first layer; laser sintering the second layer of powder material with a second laser pass at predetermined locations; wherein at least one of the matrix alloy clad filler particles sinter, and in the absence of the filler particles melting; and repeating the depositing step and laser sintering step to form subsequent layers to form an abradable seal on the substrate.

公开(公告)号：US10183312B2

公开(公告)日：2019-01-22

申请号：US14706369

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Changsheng Guo

IPC: B05D5/00 ,  F01D11/12 ,  B23K1/00 ,  C09K3/14 ,  B05D3/02 ,  B23K1/005 ,  B23K1/19 ,  B23K26/34 ,  B22F3/105 ,  C22C26/00 ,  C22C29/06 ,  C22C29/12 ,  B23K35/30 ,  B22F5/04 ,  B22F7/08 ,  B23K101/00 ,  B23K103/00

Abstract: An abrasive coating for a metal airfoil tip in a gas turbine engine may include a plurality of grit particles coated with a braze alloy material and configured for attachment to the airfoil tip. The braze alloy may be a nickel base, cobalt base or iron base braze alloy or mixtures thereof, or a titanium base braze alloy.

公开(公告)号：US10167733B2

公开(公告)日：2019-01-01

申请号：US14763001

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Shahram Amini ,  Christopher W. Strock ,  Sergei F. Burlatsky ,  Dmitri Novikov

IPC: F01D25/04 ,  F01D25/00 ,  F01D9/02 ,  F01D5/16 ,  F01D5/28

Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

公开(公告)号：US20180274120A1

公开(公告)日：2018-09-27

申请号：US15988109

申请日：2018-05-24

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  James O. Hansen

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

CPC classification number: C25D11/16 ,  C25D11/022 ,  C25D11/18 ,  C25D11/24 ,  F01D5/02 ,  F01D5/20 ,  F01D5/286 ,  F01D5/288 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/307 ,  F05D2240/31 ,  F05D2250/61 ,  F05D2300/121 ,  F05D2300/2112 ,  F05D2300/506

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：US20180230842A1

公开(公告)日：2018-08-16

申请号：US15465710

申请日：2017-03-22

Applicant: United Technologies Corporation

Inventor： Xuan Liu ,  Christopher W. Strock

IPC: F01D11/12 ,  C22C9/06

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% copper, 30.0-45.0% combined nickel, cobalt, and iron with combined iron and cobalt content at most one-third of the nickel content, 2.0-8.0% aluminum, and 5.0-15.0% chromium.

公开(公告)号：US20180171462A1

公开(公告)日：2018-06-21

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

CPC classification number: C23C4/067 ,  C23C4/134 ,  F01D11/122 ,  F01D11/125 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2230/90 ,  F05D2240/55 ,  F05D2300/121 ,  F05D2300/2282 ,  F05D2300/43 ,  F05D2300/50 ,  F05D2300/611 ,  F05D2300/615 ,  F16J15/44 ,  Y02T50/672

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：US10001022B2

公开(公告)日：2018-06-19

申请号：US14394215

申请日：2014-04-21

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D11/08 ,  F01D11/00 ,  F16J15/3224 ,  F16J15/44 ,  F01D5/02 ,  F01D17/10 ,  F01D25/12

CPC classification number: F01D11/08 ,  F01D5/02 ,  F01D11/003 ,  F01D17/105 ,  F01D25/12 ,  F05D2220/323 ,  F05D2300/2281 ,  F05D2300/2284 ,  F16J15/3224 ,  F16J15/445 ,  Y02T50/672

Abstract: The present disclosure relates to a first seal for an aircraft blade outer air seal (“BOAS”) comprising a first portion comprising a first channel and a second channel, and a second portion comprising a first projection and a second projection, wherein the first projection slidably couples to the first channel and the second projection slidably couples to the second channel. The first portion and/or the second portion may be coated with a low friction substance. The first portion may be coupled to a vane support and/or a BOAS, and the second portion may be coupled to a first OAS support. The first seal may enable a radial translation of the BOAS in response to an aircraft maneuver.

公开(公告)号：US09938849B2

公开(公告)日：2018-04-10

申请号：US15026755

申请日：2014-09-17

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Paul M. Lutjen ,  Michael J. Bruskotter

IPC: F01D11/12 ,  C23C4/129 ,  C23C4/134 ,  C23C4/18 ,  C23C28/00 ,  F01D11/02 ,  F16J15/40

CPC classification number: F01D11/122 ,  C23C4/129 ,  C23C4/134 ,  C23C4/18 ,  C23C28/32 ,  C23C28/3455 ,  F01D11/02 ,  F05D2220/32 ,  F05D2230/312 ,  F05D2240/11 ,  F05D2240/55 ,  F16J15/40

Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.

公开(公告)号：US20180044771A1

公开(公告)日：2018-02-15

申请号：US15235346

申请日：2016-08-12

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: C23C4/02 ,  F01D5/28 ,  C23C4/12

CPC classification number: C23C4/02 ,  B05B7/16 ,  B23K26/3584 ,  B23K26/361 ,  B23K26/362 ,  C23C4/12 ,  C23C28/00 ,  F01D5/288 ,  F01D11/122 ,  F05D2220/36 ,  F05D2230/13 ,  F05D2230/31 ,  F05D2240/14 ,  F05D2240/307 ,  F05D2300/121 ,  F05D2300/611

Abstract: A process of preparing a blade tip for abrasive coating comprising: forming a hydroxide layer on a surface of the blade tip; ablating the hydroxide layer from the surface with a laser; and roughening the surface with the laser after the hydroxide layer ablation.