公开(公告)号：US20240084703A1

公开(公告)日：2024-03-14

申请号：US18239532

申请日：2023-08-29

Applicant: General Electric Company

Inventor： Atanu Saha ,  Hrishikesh Keshavan ,  Mamatha Nagesh ,  Ambarish J. Kulkarni ,  Bernard P. Bewlay

IPC: F01D5/00 ,  F01D5/28

CPC classification number: F01D5/005 ,  F01D5/288 ,  F05D2230/80 ,  F05D2300/2118 ,  F05D2300/611

Abstract: Methods for repairing a thermal barrier coating deposited on a component with localized spallation of the thermal barrier coating includes depositing a primer slurry on a thermally grown oxide of the component exposed by the localized spallation, depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes at least one of a metal and a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond between the primer and the thermally grown oxide and a second chemical bond between the primer and the ceramic material.

公开(公告)号：US11913383B2

公开(公告)日：2024-02-27

申请号：US17615895

申请日：2020-06-12

Applicant: Mitsubishi Power, Ltd.

Inventor： Yoshifumi Okajima ,  Masahiko Mega ,  Taiji Torigoe ,  Atsushi Moriwaki ,  Hiroshi Makigano ,  Koichi Tanimoto

IPC: F02C7/24 ,  C23C4/073 ,  C23C4/134 ,  G01N25/18 ,  F01D5/28 ,  F01D17/08 ,  F01D21/00

CPC classification number: F02C7/24 ,  C23C4/073 ,  C23C4/134 ,  F01D5/288 ,  F01D17/085 ,  F01D21/003 ,  G01N25/18 ,  F05D2220/32 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2260/231 ,  F05D2270/80 ,  F05D2300/2118 ,  F05D2300/514 ,  F05D2300/611

Abstract: The present invention provides a thermal barrier coated component, monitoring or evaluation of the soundness of which is able to be adequately carried out on the basis of the thermal boundary conditions that are detected by a sensor. A thermal barrier coated component according to the present invention comprises: a base material; a first bond coat layer that is a metal bonding layer formed on the base material; a sensor unit that comprises a sensor and a conductive wire, which are formed on the first bond coat layer; a second bond coat layer that is formed on the first bond coat layer so as to cover at least the sensor unit, while having a surface roughness higher than that of the first bond coat layer; and a top coat layer that is formed on the second bond coat layer.

公开(公告)号：US11739410B2

公开(公告)日：2023-08-29

申请号：US15624396

申请日：2017-06-15

Applicant: The Penn State Research Foundation

Inventor： Douglas E. Wolfe ,  Michael P. Schmitt

IPC: C23C28/00 ,  C23C4/11 ,  C23C10/60 ,  C23C10/28 ,  C23C10/52 ,  C23C4/134 ,  C23C14/08 ,  C23C14/30 ,  F01D5/28 ,  F01D9/04 ,  F02C7/24

CPC classification number: C23C4/11 ,  C23C4/134 ,  C23C10/28 ,  C23C10/52 ,  C23C10/60 ,  C23C14/081 ,  C23C14/30 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/288 ,  F01D9/04 ,  F02C7/24 ,  F05D2220/323 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2300/15 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/5023 ,  F05D2300/5024 ,  Y02T50/60

Abstract: High temperature stable thermal barrier coatings useful for substrates that form component parts of engines such as a component from a gas turbine engine exposed to high temperatures are provided. The thermal barrier coatings include a multiphase composite and/or a multilayer coating comprised of two or more phases with at least one phase providing a low thermal conductivity and at least one phase providing mechanical and erosion durability. Such low thermal conductivity phase can include a rare earth zirconate and such mechanical durability phase can include a rare earth a rare earth aluminate. The different phases are thermochemically compatible even at high temperatures above about 1200° C.

公开(公告)号：US20190234220A1

公开(公告)日：2019-08-01

申请号：US16313992

申请日：2017-09-25

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Daisuke YOSHIDA ,  Taiji TORIGOE ,  Masaki TANEIKE ,  Naotoshi OKAYA ,  Yoshiyuki INOUE

IPC: F01D5/28 ,  C23C28/04 ,  C23C4/02 ,  C23C4/073 ,  C23C4/11 ,  C23C4/18

CPC classification number: F01D5/288 ,  C23C4/02 ,  C23C4/073 ,  C23C4/11 ,  C23C4/18 ,  C23C28/00 ,  C23C28/042 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00 ,  F05D2230/40 ,  F05D2230/90 ,  F05D2300/175 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/611 ,  F05D2300/701

Abstract: A method for producing a turbine blade includes forming an undercoat on a surface of a base material of a turbine blade, which is formed of a Ni-based alloy material, the undercoat being formed of a metallic material having a higher oxidation-resisting property than that of the base material, performing diffusing treatment for heating the base material having the undercoat formed thereon and diffusing a part of the undercoat on the base material side, and forming a topcoat on a surface of the undercoat after the diffusing treatment is performed, the topcoat being formed of a material having a lower thermal conductivity than that of the base material and the undercoat.

公开(公告)号：US20180355489A1

公开(公告)日：2018-12-13

申请号：US15619599

申请日：2017-06-12

Applicant: United Technologies Corporation

Inventor： Kevin Seymour ,  Christopher W. Strock

IPC: C23C28/00 ,  F01D25/00

CPC classification number: C23C28/3455 ,  C23C28/321 ,  C23C28/3215 ,  C23C30/00 ,  F01D5/288 ,  F01D5/34 ,  F01D11/001 ,  F01D25/005 ,  F05D2230/53 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/605 ,  F05D2300/609 ,  F05D2300/611

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.

公开(公告)号：US20180274387A1

公开(公告)日：2018-09-27

申请号：US15465995

申请日：2017-03-22

Applicant: The Boeing Company

Inventor： Scott D. Hartshorn ,  Keith D. Humfeld

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

CPC classification number: C23C28/042 ,  C23C28/046 ,  C23C28/322 ,  C23C28/3455 ,  F01D5/02 ,  F01D5/08 ,  F01D25/12 ,  F01D25/26 ,  F05D2300/20 ,  F05D2300/2102 ,  F05D2300/2118 ,  F05D2300/5024 ,  Y02T50/673 ,  Y02T50/676

Abstract: An engine shaft assembly for an engine is provided. The engine shaft assembly includes a shaft and a thermal distribution layer. The thermal distribution layer is provided on the shaft, and is configured to minimize the effect of distortion of the shaft caused by asymmetric cooling on shutdown of the engine.

公开(公告)号：US20180066348A1

公开(公告)日：2018-03-08

申请号：US15802837

申请日：2017-11-03

Applicant: United Technologies Corporation

Inventor： Christopher W. Strock ,  Matthew E. Bintz

IPC: C23C4/02 ,  C22C27/04 ,  C22C27/06 ,  C23C28/00 ,  F01D11/12 ,  C23C4/11 ,  F04D29/32 ,  F04D29/16 ,  F04D29/02 ,  C23C4/134 ,  F04D29/52 ,  F01D5/28 ,  C22C27/02

CPC classification number: C23C4/02 ,  C22C27/025 ,  C22C27/04 ,  C22C27/06 ,  C23C4/11 ,  C23C4/134 ,  C23C28/321 ,  C23C28/3455 ,  C23C28/347 ,  F01D5/288 ,  F01D11/122 ,  F04D29/023 ,  F04D29/164 ,  F04D29/321 ,  F04D29/526 ,  F05D2230/312 ,  F05D2240/11 ,  F05D2300/174 ,  F05D2300/2118

Abstract: A blade outer air seal (BOAS) or segment thereof comprises: a metallic substrate having an inner diameter (ID) surface; and a coating system along the inner diameter surface comprises: a bondcoat atop the substrate; and a ceramic barrier coat atop the bondcoat. The bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight.

公开(公告)号：US20170198601A1

公开(公告)日：2017-07-13

申请号：US14993140

申请日：2016-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael N. Task ,  Mark A. Boeke ,  Jeffrey R. Levine ,  Russell J. Bergman

IPC: F01D25/00 ,  C23C14/16 ,  F01D9/04 ,  C23C14/35 ,  C23C14/30 ,  C22C19/05 ,  C23C14/08

CPC classification number: F01D25/005 ,  C22C19/05 ,  C22C19/056 ,  C22C19/057 ,  C23C14/083 ,  C23C14/16 ,  C23C14/30 ,  C23C14/35 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2240/128 ,  F05D2260/231 ,  F05D2300/17 ,  F05D2300/175 ,  F05D2300/182 ,  F05D2300/2118 ,  F05D2300/611

Abstract: A gas turbine engine component comprising a nozzle segment, the nozzle segment comprising at least one substrate having a surface. A metallic bondcoat is coupled to the surface of the substrate. An yttria-stabilized zirconia thermal barrier coating is coupled to the metallic bondcoat opposite the surface.

公开(公告)号：US20170145836A1

公开(公告)日：2017-05-25

申请号：US14950718

申请日：2015-11-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Shankar Sivaramakrishnan ,  Larry Steven Rosenzweig

IPC: F01D5/28 ,  C23C4/134

CPC classification number: F01D5/288 ,  C23C4/073 ,  C23C4/11 ,  C23C4/134 ,  C23C28/3215 ,  C23C28/3455 ,  F05D2300/2118 ,  Y02T50/671 ,  Y02T50/6765

Abstract: An article having a damage-tolerant thermal barrier coating includes a plurality of coating layers disposed over a substrate. The plurality of coatings comprises an inner layer and an outer layer. The outer layer is more resistant to infiltration by nominal CMAS relative to 8 weight percent yttria-stabilized zirconia at a temperature of 1300 degrees Celsius. The inner layer has, in a temperature range from about 1000 degrees Celsius to about 1200 degrees Celsius, a thermal resistance in a range from about 9×10−5 degree Kelvin per watt to about 23×10−5 degree Kelvin per watt.

公开(公告)号：US20170002667A1

公开(公告)日：2017-01-05

申请号：US15198915

申请日：2016-06-30

Applicant: Airbus Defence and Space GmbH

Inventor： Juergen STEINWANDEL ,  Ning WANG ,  Helmut PIRINGER

IPC: F01D5/28 ,  B28B11/24 ,  C23C16/30 ,  B28B1/24 ,  C23C16/442 ,  C23C16/04

CPC classification number: F01D5/282 ,  B28B1/24 ,  B28B11/243 ,  C04B35/053 ,  C04B35/117 ,  C04B35/486 ,  C04B35/505 ,  C04B35/62857 ,  C04B35/6286 ,  C04B35/62863 ,  C04B35/62865 ,  C04B35/62894 ,  C04B35/62897 ,  C04B35/6348 ,  C04B35/76 ,  C04B35/803 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/614 ,  C04B2235/616 ,  C23C16/045 ,  C23C16/30 ,  C23C16/32 ,  C23C16/442 ,  F01D5/284 ,  F01D5/288 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/226 ,  F05D2300/228 ,  F05D2300/44 ,  F05D2300/601 ,  F05D2300/6033

Abstract: This relates to a turbine blade comprising a preformed fibrous fabric of fibres consisting of carbon, silicon carbide or rhenium fixed with a binder resin, and wherein the preformed and fixed fibrous fabric is coated and infiltrated, respectively, with B4C, wherein the preformed fibrous fabric that has been fixed and coated and infiltrated, respectively, with B4C further has a multilayer coating consisting of at least one layer of silicon carbide and at least one layer of a metal boride, a metal nitride or a metal carbide, and wherein an oxide ceramic is applied over the multilayer coating. The turbine blade is resistant to high temperatures and is particularly well suited for use in a gas turbine. Methods for producing the turbine blade are also described.

Abstract translation: 这涉及一种涡轮叶片，其包括由碳，碳化硅或铼固定的纤维组成的纤维织物预先形成的纤维织物，所述纤维织物用粘合剂树脂固定，并且其中预先形成的和固定的纤维织物分别用B4C涂覆和渗透，其中预成型纤维织物 已经用B4C分别固定和涂覆和渗透的多层涂层进一步具有由至少一层碳化硅和至少一层金属硼化物，金属氮化物或金属碳化物组成的多层涂层，并且其中氧化物陶瓷 施加在多层涂层上。 涡轮叶片耐高温，特别适用于燃气轮机。 还描述了用于生产涡轮叶片的方法。