公开(公告)号：US20180030993A1

公开(公告)日：2018-02-01

申请号：US15223460

申请日：2016-07-29

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F04D29/16 ,  F04D29/52 ,  B23P15/02

Abstract: A blade outer airseal comprising a body having: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; a trailing end; 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 filler. The filler forms at least 20% by volume of the abradable layer with agglomerates or aggregates of oxide particles, the oxide particles having a D50 size ≦200 nm.

公开(公告)号：US20170276007A1

公开(公告)日：2017-09-28

申请号：US15078978

申请日：2016-03-23

Applicant: United Technologies Corporation

Inventor： Philip R. Rioux ,  Nicholas R Leslie ,  Paul M. Lutjen ,  Christopher W. Strock

IPC: F01D11/12 ,  F04D29/32 ,  F01D25/00 ,  F16J15/44 ,  F01D5/28

CPC classification number: F01D11/122 ,  F01D5/28 ,  F01D25/005 ,  F04D29/164 ,  F04D29/324 ,  F04D29/526 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/11 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2300/175 ,  F05D2300/20 ,  F05D2300/6032 ,  F16J15/44 ,  F16J15/445 ,  Y02T50/672 ,  Y02T50/6765

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 and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.

公开(公告)号：US09528008B2

公开(公告)日：2016-12-27

申请号：US14771893

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher W. Strock ,  Michael J. Maloney

IPC: C23C30/00 ,  C09D5/08 ,  C23C4/04 ,  C08K3/08 ,  C08K3/38

CPC classification number: C09D5/08 ,  C08K3/08 ,  C08K3/38 ,  C08K2003/0812 ,  C08K2003/0862 ,  C08K2003/0881 ,  C08K2003/385 ,  C23C4/04 ,  C23C30/00

Abstract: An abradable coating for application to a gas turbine engine part is formed from a titanium aluminide alloy, a filler material, and porosity. The coating may be applied to a part such as a casing made from a titanium alloy.

Abstract translation: 用于燃气涡轮发动机部件的可磨损涂层由钛铝化合物，填料和孔隙形成。 可以将涂层施加到诸如由钛合金制成的外壳的部件上。

公开(公告)号：US20160355921A1

公开(公告)日：2016-12-08

申请号：US14728631

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Charles R. Beaudoin ,  Christopher W. Strock

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

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.

Abstract translation: 用于燃气涡轮发动机的气密封。 密封件包括热喷涂的耐磨密封层。 可磨损材料由形成金属基体的铝粉末和在金属基体中作为填料嵌入的共沉积甲基丙烯酸甲酯颗粒和/或六方氮化硼颗粒组成。

公开(公告)号：US20160347671A1

公开(公告)日：2016-12-01

申请号：US15101976

申请日：2014-11-14

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: C04B35/622 ,  C23C14/30 ,  F01D5/28 ,  F23R3/28 ,  F01D11/08 ,  F01D25/00 ,  F23R3/00 ,  C23C4/04 ,  F01D9/02

CPC classification number: C04B35/62222 ,  C23C4/04 ,  C23C4/11 ,  C23C4/18 ,  C23C14/083 ,  C23C14/30 ,  C23C14/5846 ,  F01D5/288 ,  F01D9/023 ,  F01D11/08 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2300/134 ,  F05D2300/15 ,  F05D2300/21 ,  F05D2300/5023 ,  F05D2300/6033 ,  F23R3/002 ,  F23R3/28

Abstract: The thermal barrier coating includes reactive gadolinia in its microstructures and the embedded gadolinia effectively reacts with CMAS contaminant reducing the damage from CMAS. Moreover, a method to produce a CMAS resistant thermal barrier coating can include a post-treatment to the thermal barrier coating with the reactive gadolinia suspension in sol-gel state.

Abstract translation: 热障涂层在其微观结构中包括反应性钆，并且嵌入的氧化钆与CMAS污染物有效反应以减少CMAS的损害。 此外，生产CMAS耐热隔热涂层的方法可以包括在溶胶凝胶状态下用反应性钆悬浮液对热障涂层进行后处理。

公开(公告)号：US20160305258A1

公开(公告)日：2016-10-20

申请号：US14687651

申请日：2015-04-15

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F01D5/28 ,  B05B7/14 ,  B05D3/00 ,  B05D1/02

CPC classification number: F01D5/288 ,  B05B7/1481 ,  B05D1/02 ,  B05D1/12 ,  B05D1/34 ,  B05D3/007 ,  B05D5/00 ,  C23C30/00 ,  F01D5/20 ,  F01D11/122 ,  F01D11/125 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/307 ,  F05D2300/134 ,  F05D2300/43 ,  F05D2300/611 ,  Y02T50/672

Abstract: A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abraisive filler between about 50%-75% by volume of the abrasive coating.

Abstract translation: 用于燃气涡轮发动机的部件包括一个翼型部分，该翼型部分包括喷射在自由端上的自由端和磨料涂层，所述研磨涂层包括聚合物基体和磨料填料，所述磨损填料为约50％-75％ 磨料涂层。

公开(公告)号：US20160290151A1

公开(公告)日：2016-10-06

申请号：US15037127

申请日：2014-11-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher W. Strock ,  Enzo DiBenedetto

IPC: F01D11/08 ,  F01D25/24 ,  C23C4/134 ,  F01D5/12

Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.

Abstract translation: 密封件包括壳体。 涂层具有至少两层，其中结合层定位在壳体和第二硬质层之间。 第二硬层形成为比接合层更硬。 接合层具有大于或等于200psi且小于或等于2000psi的粘合强度。 还公开了一种燃气涡轮发动机，以及形成涂层的方法。

公开(公告)号：US20160236989A1

公开(公告)日：2016-08-18

申请号：US14623803

申请日：2015-02-17

Applicant: United Technologies Corporation

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

IPC: C04B35/622 ,  C23C14/22 ,  C23C4/12

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.

Abstract translation: 根据本公开的一个实施例，涂层包括多个细长的增强材料。 涂层包括其中嵌入第一细长增强材料的第一部分的粘合涂层。 涂层还包括邻近粘合涂层的陶瓷涂层，其中嵌入有第一细长增强材料的第二部分。

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：US20160123160A1

公开(公告)日：2016-05-05

申请号：US14923574

申请日：2015-10-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D5/28 ,  B32B9/04 ,  B32B3/12 ,  F01D9/04 ,  C23C4/12 ,  B32B37/12 ,  F01D11/08 ,  F01D25/08 ,  B32B9/00 ,  B32B7/12

Abstract: A thermal barrier system includes a protective coating on a substrate, and a ceramic feature layer attached to the protective coating via an adhesive spray coat.

Abstract translation: 热障系统包括在基底上的保护涂层和通过粘合剂喷涂附着到保护涂层上的陶瓷特征层。