公开(公告)号：US11125102B2

公开(公告)日：2021-09-21

申请号：US16539217

申请日：2019-08-13

Applicant: United Technologies Corporation

Inventor： Shahram Amini ,  Christopher W. Strock ,  Weina Li

IPC: F01D11/12 ,  B22F1/02 ,  B22F7/08 ,  C22C1/04 ,  C23C4/12 ,  C23C18/16 ,  F02C7/28

Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.

公开(公告)号：US11118257B2

公开(公告)日：2021-09-14

申请号：US15033153

申请日：2014-10-27

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: C23C4/134 ,  C23C4/02 ,  C23C4/18 ,  C23C4/10 ,  F01D5/28 ,  F23R3/00 ,  C23C4/04

Abstract: A method of manufacturing a fiber reinforced coating. The method includes providing a substrate and plasma spraying a ceramic matrix having fibers encapsulated in a precursor material onto the substrate.

公开(公告)号：US11111807B2

公开(公告)日：2021-09-07

申请号：US16717458

申请日：2019-12-17

Applicant: United Technologies Corporation

Inventor： Kevin Seymour ,  Christopher W. Strock

IPC: F01D11/12 ,  F01D5/02 ,  F04D29/32 ,  F04D29/08 ,  C23C4/134

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：US11066937B2

公开(公告)日：2021-07-20

申请号：US16825610

申请日：2020-03-20

Applicant: United Technologies Corporation

Inventor： Changsheng Guo ,  Christopher W. Strock

IPC: F01D5/20 ,  F01D11/12

Abstract: An integrally bladed rotor, including: a plurality of blades integrally formed with a hub as a single component, each of the plurality of blades having a blade body extending from the hub to an opposed blade tip surface along a longitudinal axis, wherein the blade body defines a pressure side and a suction side, and wherein the blade body includes a cutting edge defined between the blade tip surface of the blade body and the pressure side of the blade body, wherein the cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing an integrally bladed rotor includes: forming a plurality of airfoils integrally with a hub to form a single component, each of the plurality of airfoils having an opposed tip surface with respect to the hub extending along a longitudinal axis, wherein each of the plurality of airfoils defines a pressure side and a suction side; and forming a cutting edge between the tip surface and the pressure side of each of the plurality of airfoils, wherein the cutting edge is configured to abrade a seal section of an engine case.

公开(公告)号：US11028721B2

公开(公告)日：2021-06-08

申请号：US16039907

申请日：2018-07-19

Applicant: United Technologies Corporation

Inventor： Kevin Seymour ,  Christopher W. Strock ,  Thomas D. Kasprow

IPC: F01D11/12 ,  B32B7/05 ,  B32B5/16 ,  B32B7/12 ,  F01D5/14 ,  F01D5/28

Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 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; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.

公开(公告)号：US10934217B2

公开(公告)日：2021-03-02

申请号：US16443452

申请日：2019-06-17

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: C04B35/622 ,  C23C4/18 ,  C23C14/08 ,  C23C14/58 ,  F01D5/28 ,  C23C4/11 ,  C23C4/04 ,  C23C14/30 ,  F01D9/02 ,  F01D11/08 ,  F01D25/00 ,  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.

公开(公告)号：US10760443B2

公开(公告)日：2020-09-01

申请号：US15948596

申请日：2018-04-09

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 scal 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：US10711622B2

公开(公告)日：2020-07-14

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

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：US20200149431A1

公开(公告)日：2020-05-14

申请号：US16598552

申请日：2019-10-10

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D25/24 ,  C23C28/00 ,  F01D11/12 ,  B23P15/00 ,  B23K1/19 ,  B23K1/00

Abstract: A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.

公开(公告)号：US20200149426A1

公开(公告)日：2020-05-14

申请号：US16184108

申请日：2018-11-08

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F01D11/12

Abstract: An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.