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公开(公告)号：US20160040548A1
公开(公告)日：2016-02-11
申请号：US14812668
申请日：2015-07-29
Applicant: United Technologies Corporation
Inventor： Jose R. Paulino , Christopher W. Strock
CPC classification number: C23C4/12 , F01D11/122 , F05D2230/90 , F05D2240/11 , F05D2300/20
Abstract: A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion.
Abstract translation: 一种燃气涡轮发动机制品包括基材和粘合涂层，其覆盖基材的至少一部分，所述台阶形成在基材和粘结涂层中的至少一个中。 绝缘面漆设在接合涂层上。 绝热顶涂层包括由至少一个断层隔开的第一顶涂层部分，其从第二顶涂层部分延伸穿过绝热顶涂层。
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公开(公告)号：US20160032737A1
公开(公告)日：2016-02-04
申请号：US14774573
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher W. Strock
CPC classification number: F01D5/288 , F01D5/284 , F01D11/08 , F01D11/122 , F01D25/24 , F05D2220/32 , F05D2230/31 , F05D2240/307 , F05D2300/171 , F05D2300/173 , F05D2300/177 , F05D2300/2106 , F05D2300/211 , F05D2300/2112 , F05D2300/2118 , F05D2300/506 , F05D2300/6032 , F05D2300/611 , Y02T50/673
Abstract: A method of preventing transfer of metal of a gas turbine rotor blade having a metal tip to a blade outer air seal coating on a gas turbine case includes forming a coating on the metal tip. The coating comprises a bond coat layer on the metal tip and a ceramic filled metallic layer having a ceramic component in a matrix of a metal MCr, MCrAl, MCrAlY or a refractory modified CMCrAlY where M is nickel, cobalt, iron or mixtures thereof.
Abstract translation: 一种防止具有金属尖端的燃气轮机转子叶片的金属转移到燃气轮机壳体上的叶片外部空气密封涂层的方法包括在金属尖端上形成涂层。 涂层包括在金属尖端上的粘合涂层和陶瓷填充金属层，其中金属MCr，MCrAl，MCrAlY或难熔改性CMCrAlY的基体中具有陶瓷成分，其中M是镍，钴，铁或其混合物。
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143.发明申请ALUMINUM BASED ABRADABLE MATERIAL WITH REDUCED METAL TRANSFER TO BLADES 审中-公开基于铝的可磨损材料，具有减少的金属转移到叶片公开(公告)号：US20140093360A1
公开(公告)日：2014-04-03
申请号：US13632657
申请日：2012-10-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher W. Strock
CPC classification number: B22F5/04 , C22C21/02 , C22C32/00 , F01D11/122 , F05D2300/121 , F05D2300/6032 , Y02T50/672
Abstract: A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and having a melting point higher than a melting point of the melting point of the abradable coating matrix alloy.
Abstract translation: 涡轮机具有与多个翼型配合的密封。 该密封件是由可磨蚀的铝基材料形成的，该铝基材料具有嵌入其中的多个硬质相颗粒，其熔点高于可磨损涂层基体合金的熔点的熔点。
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公开(公告)号：US11149338B2
公开(公告)日：2021-10-19
申请号：US16397092
申请日：2019-04-29
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Shahram Amini
IPC: C23C4/06 , F01D25/00 , F02C7/24 , F01D5/28 , C04B41/87 , C04B41/00 , C04B41/50 , C23C4/18 , C23C14/18 , C23C4/10 , C23C28/04
Abstract: A method of providing a self-healing coating includes providing substrate, applying a layer of an aluminum-containing MAX phase material and another material to the substrate. The method includes exposing the layer to a temperature greater than 2000° F. to form alpha aluminum.
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145.发明授权公开(公告)号：US11015474B2
公开(公告)日：2021-05-25
申请号：US16165233
申请日：2018-10-19
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
Abstract: A turbine article includes a substrate with a geometric surface having a multiple of divots recessed into the substrate, and a ceramic topcoat disposed over the geometric surface, the topcoat including at least a first layer having a first hardness and a second layer having a second hardness, the first hardness different than the second hardness.
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Patent Agency Ranking
公开(公告)号：US10895167B2
公开(公告)日：2021-01-19
申请号：US15608028
申请日：2017-05-30
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Christopher W. Strock
Abstract: A turbine may include a blade coupled to a rotor, a vane upstream from the blade and coupled to a vane support that defines a metering hole, and a blade outer air seal disposed radially outward from the blade and downstream from the vane support. An impingement surface may be disposed between the vane support and the blade outer air seal. The impingement surface may be oriented at an angle to the metering hole of between 50 degrees and 5 degrees.
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147.发明授权公开(公告)号：US10774669B2
公开(公告)日：2020-09-15
申请号：US16170476
申请日：2018-10-25
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
Abstract: An air seal in a gas turbine engine comprising a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a soft ceramic material.
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公开(公告)号：US10731260B2
公开(公告)日：2020-08-04
申请号：US15619599
申请日：2017-06-12
Applicant: United Technologies Corporation
Inventor： Kevin Seymour , Christopher W. Strock
Abstract: A gas turbine engine includes a rotor that has a rim, blades extending radially outwards from the rim, a hub extending radially inwards from the rim, an arm extending axially from the rim, the arm having a radially outer surface, and a coating disposed on the radially outer surface. The coating is zirconia-toughened alumina in which the alumina is a matrix with grains of the zirconia dispersed there through. The grains of zirconia are predominantly a tetragonal crystal structure.
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公开(公告)号：US10711638B2
公开(公告)日：2020-07-14
申请号：US16237065
申请日：2018-12-31
Applicant: United Technologies Corporation
Inventor： Shahram Amini , Christopher W. Strock , Sergei F. Burlatsky , Dmitri Novikov
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.
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150.发明授权公开(公告)号：US10662517B2
公开(公告)日：2020-05-26
申请号：US15235346
申请日：2016-08-12
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
IPC: C23C4/02 , B23K26/352 , C23C4/12 , F01D5/28 , C23C28/00 , B23K26/361 , B05B7/16 , B23K26/362 , F01D11/12
Abstract: A process of preparing a blade tip for abrasive coating includes forming a hydroxide layer on a surface of the blade tip. The process includes ablating the hydroxide layer from the surface with a laser. The process includes roughening the surface with the laser after the hydroxide layer ablation.
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