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公开(公告)号：US20200024975A1
公开(公告)日：2020-01-23
申请号：US16039901
申请日：2018-07-19
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Kevin Seymour
Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material and a thermal barrier coating material applied over said film of oxidant resistant coating.
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公开(公告)号：US10539036B2
公开(公告)日：2020-01-21
申请号：US14592196
申请日：2015-01-08
Applicant: United Technologies Corporation
Inventor： Shahram Amini , Christopher W. Strock
Abstract: A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon. An abradable seal circumscribes the blades and includes a polymeric matrix with a dispersion of a nanolayer material.
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公开(公告)号：US10525529B2
公开(公告)日：2020-01-07
申请号：US15417873
申请日：2017-01-27
Applicant: United Technologies Corporation
Inventor： Pantcho P. Stoyanov , Christopher W. Strock , Thomas J. Watson
Abstract: A coated article comprising: a substrate; and a coating on the substrate comprising: a metallic matrix comprising, by weight: Al as a largest constituent; 3.0-6.0 Cr; 1.5-4.0 Mn; 0.1-3.5 Co; and 0.3-2.0 Zr; and a filler and optionally porosity.
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公开(公告)号：US20200003225A1
公开(公告)日：2020-01-02
申请号：US16565269
申请日：2019-09-09
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Changsheng Guo
Abstract: A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.
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75.发明申请公开(公告)号：US20190308910A1
公开(公告)日：2019-10-10
申请号：US16443452
申请日：2019-06-17
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
IPC: C04B35/622 , F01D11/08 , C23C14/08 , F01D25/00 , C23C4/18 , C23C4/11 , C23C14/58 , F01D5/28 , F01D9/02 , C23C14/30 , C23C4/04 , F23R3/00 , 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.
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Patent Agency Ranking
公开(公告)号：US10315249B2
公开(公告)日：2019-06-11
申请号：US15223480
申请日：2016-07-29
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
Abstract: A method for manufacturing a powder comprises vaporizing a solvent; passing a metallic powder and a polymer powder through the solvent vapor to mix the metallic powder with the polymer powder; and removing the solvent.
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公开(公告)号：US10309233B2
公开(公告)日：2019-06-04
申请号：US15943991
申请日：2018-04-03
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
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.
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公开(公告)号：US10294962B2
公开(公告)日：2019-05-21
申请号：US15638486
申请日：2017-06-30
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
Abstract: A gas turbine engine includes an inlet duct, a compressor section, a combustor section, and a turbine section connected to drive the compressor section. The compressor section includes circumferentially-spaced blades having abrasive blade tips. A seal is disposed radially outwards of the blades. The seal includes a substrate that has a substrate hardness, an abradable layer that has an abradable layer hardness, and a hard interlayer between the substrate and the abradable layer. The hard interlayer has an interlayer hardness that is higher than the abradable layer hardness and higher than the substrate hardness.
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公开(公告)号：US20190085865A1
公开(公告)日：2019-03-21
申请号：US15708711
申请日：2017-09-19
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock
Abstract: A seal for a gas turbine engine including an interlayer between a substrate and an abradable layer, the interlayer containing abrasive particles of which at least some abrasive particles protrude out of an interface that abuts the abradable layer.
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80.发明申请公开(公告)号：US20190063251A1
公开(公告)日：2019-02-28
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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