公开(公告)号：US10060281B2

公开(公告)日：2018-08-28

申请号：US14862430

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： Christopher W Strock ,  Changsheng Guo ,  Yan Chen

IPC: F01D11/12 ,  C22C19/05 ,  C22C9/01 ,  C22C9/00 ,  C22C9/06

CPC classification number: F01D11/122 ,  C22C9/00 ,  C22C9/01 ,  C22C9/06 ,  C22C19/055 ,  F05D2300/172 ,  Y02T50/672

Abstract: What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material.

公开(公告)号：US09850767B2

公开(公告)日：2017-12-26

申请号：US14711237

申请日：2015-05-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Changsheng Guo ,  Yan Chen

IPC: F02C3/04 ,  F01D5/28 ,  F01D5/14 ,  B05D7/14 ,  F01D11/12 ,  F02K3/06

CPC classification number: F01D5/288 ,  B05D7/14 ,  F01D5/147 ,  F01D11/122 ,  F02K3/06 ,  F05D2230/90 ,  F05D2300/611

Abstract: A fan blade for a gas turbine engine is described. The fan blade may comprise a body portion formed from a metallic material, and it may include a suction side, a pressure side, a leading edge, a trailing edge, and a tip. A coating may be applied to the tip, and the coating may have a thermal conductivity of no more than about 10 watt per meter kelvin. The coating may be a thermal barrier coating comprising yttria-stabilized zirconia.

公开(公告)号：US20160312897A1

公开(公告)日：2016-10-27

申请号：US14692786

申请日：2015-04-22

Applicant: United Technologies Corporation

Inventor： Scott Alan Eastman ,  Changsheng Guo

IPC: F16J15/34 ,  C08L79/08 ,  F01D11/00 ,  C08K7/24

CPC classification number: F01D11/122 ,  C08K7/24 ,  F01D11/125 ,  F01D11/127 ,  F05D2240/55 ,  F05D2300/10 ,  F05D2300/43 ,  F16J15/44 ,  F16J15/444 ,  Y02T50/671

Abstract: An abradable seal includes a seal element that is formed of a polymer matrix with thermally conductive microspheres dispersed through the polymer matrix. The polymer matrix has a polymer matrix thermal conductivity and the microspheres have a microsphere thermal conductivity that is greater than the polymer matrix thermal conductivity.

Abstract translation: 可磨损的密封件包括密封元件，该密封元件由聚合物基体形成，其中分散有聚合物基质的导热微球体。 聚合物基质具有聚合物基质导热性，并且微球具有大于聚合物基质热导率的微球导热系数。

公开(公告)号：US20160169013A1

公开(公告)日：2016-06-16

申请号：US14934458

申请日：2015-11-06

Applicant: United Technologies Corporation

Inventor： Changsheng Guo ,  Christopher W. Strock

IPC: F01D9/04 ,  F16J15/3204 ,  C23C16/02 ,  F16J15/328 ,  C25D11/04 ,  C23C16/27 ,  C23C16/56 ,  C23C28/04 ,  B23H1/10 ,  F01D11/00 ,  C23C16/34

CPC classification number: F01D9/041 ,  B23H1/10 ,  B23H9/008 ,  B23H9/10 ,  C23C16/0263 ,  C23C16/27 ,  C23C16/34 ,  C23C16/56 ,  C23C28/046 ,  C25D11/04 ,  F01D5/20 ,  F01D5/28 ,  F01D5/288 ,  F01D11/001 ,  F01D11/12 ,  F01D11/122 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2230/314 ,  F05D2230/90 ,  F05D2240/121 ,  F05D2240/125 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/177 ,  F05D2300/224 ,  F05D2300/611 ,  F16J15/3204 ,  F16J15/328

Abstract: A component for a gas turbine engine is described. The component may comprise a body portion formed from a metallic material. The component may further comprise an abrasive surface forming at least one surface of the body portion, and the abrasive surface may be configured to abrade an abradable material. The abrasive surface may be formed from electrical discharge machining of the metallic material.

Abstract translation: 描述了用于燃气涡轮发动机的部件。 该部件可以包括由金属材料形成的主体部分。 所述部件还可包括形成所述主体部分的至少一个表面的研磨表面，并且所述研磨表面可构造成研磨可磨损材料。 研磨表面可以由金属材料的放电加工形成。

公开(公告)号：US20150337671A1

公开(公告)日：2015-11-26

申请号：US14706369

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Changsheng Guo

IPC: F01D5/28 ,  B05D3/02 ,  B05D5/00 ,  C09K3/14

CPC classification number: B05D5/00 ,  B05D3/0254 ,  B22F3/1055 ,  B22F5/04 ,  B22F7/08 ,  B23K1/0018 ,  B23K1/0056 ,  B23K1/19 ,  B23K26/34 ,  B23K35/3033 ,  B23K35/3046 ,  B23K35/3053 ,  B23K2101/001 ,  B23K2103/50 ,  C09K3/14 ,  C22C26/00 ,  C22C29/065 ,  C22C29/12 ,  F01D11/122 ,  F05D2230/31 ,  Y02P10/295 ,  Y02T50/672 ,  Y02T50/6765 ,  Y10T428/2438 ,  Y10T428/24388

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.

Abstract translation: 用于燃气涡轮发动机中的金属翼型头的磨料涂层可以包括涂覆有钎焊合金材料并被配置为附接到翼型端头的多个砂粒。 钎焊合金可以是镍基，钴基或铁基钎焊合金或其混合物，或钛基钎焊合金。