公开(公告)号：US20160010197A1

公开(公告)日：2016-01-14

申请号：US14772180

申请日：2014-03-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher W. Strock

IPC: C23C4/00 ,  F02C7/20

CPC classification number: F02C7/20 ,  B05B12/20 ,  B05B13/0285 ,  B05C13/02 ,  B05C21/005 ,  C23C4/01 ,  C23C4/02 ,  C23C4/11 ,  C23C14/042 ,  C23C28/3215 ,  C23C28/3455 ,  F01D25/285 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2240/90 ,  Y02T50/6765

Abstract: A fixture assembly includes a standoff, a backplate and a spray coating shield attached to a support.

Abstract translation: 夹具组件包括附接到支撑件的支座，背板和喷涂屏蔽件。

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。

公开(公告)号：US20150198056A1

公开(公告)日：2015-07-16

申请号：US14592196

申请日：2015-01-08

Applicant: United Technologies Corporation

Inventor： Shahram Amini ,  Christopher W. Strock

IPC: F01D11/12 ,  C08K3/04

CPC classification number: F01D11/122 ,  C08K3/04 ,  F01D11/125 ,  F05D2220/36 ,  F05D2230/90 ,  F05D2300/224 ,  F05D2300/226 ,  F05D2300/43 ,  F05D2300/437 ,  F05D2300/5024 ,  F05D2300/702 ,  Y02T50/672

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.

Abstract translation: 燃气涡轮发动机包括多个周向间隔开的叶片。 叶片在其上具有聚合物涂层。 可磨损的密封件围绕叶片并且包括具有纳米层材料的分散体的聚合物基质。

公开(公告)号：US11597991B2

公开(公告)日：2023-03-07

申请号：US15633114

申请日：2017-06-26

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: C23C4/06 ,  F01D11/00 ,  C23C4/12 ,  F01D11/12 ,  C23C28/00 ,  C23C4/073 ,  C23C4/11

Abstract: An abrasive coating for a substrate including a metallic based bond coat layer; a top layer; and an intermediate layer between the metallic based bond coat layer and the top layer. A method of applying an abrasive coating including applying a metallic based bond coat layer onto a substrate; grading an intermediate layer into the metallic based bond coat layer to form a graded transition between the metallic based bond coat layer and the intermediate layer; and grading a top layer into the intermediate layer to form a graded transition between the intermediate layer and the top layer.

公开(公告)号：US11572795B2

公开(公告)日：2023-02-07

申请号：US16043686

申请日：2018-07-24

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock

IPC: F01D5/28 ,  B05B7/14 ,  F01D11/12 ,  C23C30/00 ,  F04D29/02 ,  F04D29/32 ,  F01D5/20 ,  B05D1/02 ,  B05D3/00 ,  B05D5/00 ,  B05D1/12 ,  B05D1/34

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 abrasive filler between about 50%-75% by volume of the abrasive coating.

公开(公告)号：US11352890B2

公开(公告)日：2022-06-07

申请号：US15620075

申请日：2017-06-12

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Kevin W. Schlichting

IPC: F01D5/28 ,  F01D9/02 ,  F23R3/00 ,  F23R3/28 ,  F01D11/08 ,  C23C4/073 ,  C23C4/134 ,  C23C4/18 ,  C23C4/123 ,  C23C14/08 ,  C23C14/30 ,  C23C4/11 ,  C23C4/02 ,  C23C14/02 ,  C23C4/137 ,  C23C14/04 ,  C23C28/04 ,  C23C4/01 ,  C23C28/00 ,  C23C4/129

Abstract: An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

公开(公告)号：US20200325783A1

公开(公告)日：2020-10-15

申请号：US16384253

申请日：2019-04-15

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Paul M. Lutjen

IPC: F01D5/28 ,  C04B35/80

Abstract: A method of preventing spallation for a geometrically segmented thermally insulating top coat on an article, the method comprising forming a surface feature in a surface of the article; forming a crack deflection feature in the surface proximate the surface feature; disposing the thermally insulating topcoat over the surface feature; and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the surface feature.

公开(公告)号：US10794394B2

公开(公告)日：2020-10-06

申请号：US14687660

申请日：2015-04-15

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  James O. Hansen

IPC: F01D5/28 ,  F04D29/38 ,  F04D19/00 ,  C23C4/12 ,  F01D5/14 ,  F01D11/12

Abstract: A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.

公开(公告)号：US20200256206A1

公开(公告)日：2020-08-13

申请号：US16270789

申请日：2019-02-08

Applicant: United Technologies Corporation

Inventor： Paul M. Lutjen ,  Christopher W. Strock ,  Jose R. Paulino

IPC: F01D11/12

Abstract: A component for a gas turbine engine includes a surface adjacent a flow of hot gases. A plurality of cavities is in a portion of the surface. The plurality of cavities have a first group of cavities with a first cross-section and a second group of cavities with a second cross-section different from the first cross-section. The first and second groups of cavities are arranged such that there is no straight line across the portion of the surface that does not intersect one of the plurality of cavities. A thermal barrier coating is over the surface and fills each of the plurality of cavities.

公开(公告)号：US20200217209A1

公开(公告)日：2020-07-09

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.