公开(公告)号：US20180306047A1

公开(公告)日：2018-10-25

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

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：US20180223678A1

公开(公告)日：2018-08-09

申请号：US15943991

申请日：2018-04-03

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F01D5/28 ,  C23C28/04 ,  C23C24/06 ,  C23C4/06 ,  F01D11/12 ,  B05D3/00 ,  B05D1/02

CPC classification number: F01D5/288 ,  B05D1/02 ,  B05D3/007 ,  C23C4/06 ,  C23C4/08 ,  C23C24/06 ,  C23C28/044 ,  F01D11/122

Abstract: A method is disclosed for manufacturing a blade tip coating. The blade tip coating (152) comprising an abrasive (156) and a matrix (154). The method comprises forming a mixture comprising the abrasive, a precursor of the matrix, and an additional particulate (158). The mixture is pressed, the additional particulate acting as a stop to limit thickness reduction of the mixture.

公开(公告)号：US20180223677A1

公开(公告)日：2018-08-09

申请号：US15943431

申请日：2018-04-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Changsheng Guo ,  Christopher W. Strock

IPC: F01D5/20 ,  F01D11/12

CPC classification number: F01D5/20 ,  F01D11/122 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/25 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/22 ,  F05D2300/2282 ,  F05D2300/2284 ,  F05D2300/30 ,  F05D2300/506 ,  Y10T29/49337

Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

公开(公告)号：US20180222805A1

公开(公告)日：2018-08-09

申请号：US15946550

申请日：2018-04-05

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Thomas J. Martin ,  Alexander Staroselsky ,  Sergey Mironets

IPC: C04B35/622 ,  C23C4/11 ,  C23C4/18 ,  C23C14/22 ,  C23C24/08 ,  C23C28/00 ,  C25D13/22 ,  C25D13/02 ,  C23C4/073 ,  F01D5/28 ,  C23F1/04 ,  C23F4/00

CPC classification number: C04B35/62222 ,  C23C4/073 ,  C23C4/11 ,  C23C4/18 ,  C23C14/22 ,  C23C24/085 ,  C23C28/3215 ,  C23C28/324 ,  C23C28/345 ,  C23C28/3455 ,  C23F1/04 ,  C23F4/00 ,  C25D13/02 ,  C25D13/22 ,  F01D5/288 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2300/1723 ,  F05D2300/20 ,  F05D2300/614

Abstract: According to one embodiment of this disclosure, a coating includes a plurality of elongated reinforcing materials. The coating includes a bond coat in which a first portion of a first elongated reinforcing material is embedded. The coating further includes a ceramic coat adjacent the bond coat in which a second portion of the first elongated reinforcing material is embedded.

公开(公告)号：US09956580B2

公开(公告)日：2018-05-01

申请号：US14524331

申请日：2014-10-27

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Charles R. Beaudoin ,  Robert D. Richard ,  Steven G. Lemay

IPC: B05C21/00 ,  B05B15/04 ,  C23C4/02 ,  C23C4/01

CPC classification number: B05C21/005 ,  B05B12/20 ,  B05B15/60 ,  C23C4/01 ,  C23C4/02

Abstract: A mask for masking a component at an annular boundary comprises a wall (90, 92) having an inner first rim portion having a first inner diameter (D1) and an outward rebate (140) adjacent the first rim portion.

公开(公告)号：US09932839B2

公开(公告)日：2018-04-03

申请号：US14725052

申请日：2015-05-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Changsheng Guo ,  Christopher W. Strock

IPC: F01D5/20 ,  F01D11/12

CPC classification number: F01D5/20 ,  F01D11/122 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/25 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/22 ,  F05D2300/2282 ,  F05D2300/2284 ,  F05D2300/30 ,  F05D2300/506 ,  Y10T29/49337

Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

公开(公告)号：US20180030586A1

公开(公告)日：2018-02-01

申请号：US15223443

申请日：2016-07-29

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: C23C4/134 ,  C23C4/08

CPC classification number: C23C4/134 ,  B05B7/226 ,  C23C4/067 ,  C23C4/073 ,  C23C4/08 ,  C23C4/18

Abstract: A method for applying an abradable coating, comprises: generating a plasma; introducing a matrix-forming first particulate to the plasma at a first location; introducing a second particulate of an organic particulate and/or salt particulate to the plasma at a second location downstream from the first location to mix with the matrix-forming first particulate, the second particulate having a characteristic size in the range 6.0 micrometers to 45.0 micrometers; and directing the first particulate and the second particulate to a target to form a coating on the target.

公开(公告)号：US20170314410A1

公开(公告)日：2017-11-02

申请号：US15140903

申请日：2016-04-28

Applicant: United Technologies Corporation

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

IPC: F01D11/12 ,  C23C4/131 ,  C23C4/073 ,  F01D25/00 ,  F01D25/18 ,  C23C4/126 ,  C23C4/134

CPC classification number: F01D11/122 ,  B22F2998/10 ,  B22F2999/00 ,  C22C1/08 ,  C22C1/10 ,  C22C19/058 ,  C23C4/073 ,  C23C4/126 ,  C23C4/131 ,  C23C4/134 ,  F01D5/288 ,  F01D25/005 ,  F01D25/18 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2300/175 ,  F05D2300/177 ,  F05D2300/2282 ,  F05D2300/509 ,  F05D2300/514 ,  F05D2300/6032 ,  F05D2300/612 ,  F05D2300/613 ,  F05D2300/614 ,  Y02T50/672 ,  B22F5/009 ,  B22F7/06 ,  B22F7/002 ,  B22F2003/248 ,  B22F3/115 ,  B22F3/11 ,  C22C1/0433 ,  B22F1/0059 ,  B22F3/1121

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：US09657584B2

公开(公告)日：2017-05-23

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

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：US20160290150A1

公开(公告)日：2016-10-06

申请号：US14394215

申请日：2014-04-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D11/08 ,  F01D17/10 ,  F01D25/12 ,  F01D5/02

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.

Abstract translation: 本公开涉及一种用于飞行器叶片外部空气密封件（“BOAS”）的第一密封件，包括包括第一通道和第二通道的第一部分，以及包括第一突起和第二突起的第二部分，其中第一突起 可滑动地联接到第一通道，第二突出部可滑动地连接到第二通道。 第一部分和/或第二部分可以涂覆有低摩擦物质。 第一部分可以联接到叶片支撑件和/或BOAS，并且第二部分可以联接到第一OAS支撑件。 第一个密封件可以使得响应于飞行器操纵的BOAS的径向平移。