公开(公告)号：US20230304410A1

公开(公告)日：2023-09-28

申请号：US18093081

申请日：2023-01-04

Applicant: Raytheon Technologies Corporation

Inventor： Christopher W. Strock

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

CPC classification number: F01D5/288 ,  B05B7/1481 ,  B05D1/02 ,  B05D3/007 ,  C23C30/00 ,  F01D5/20 ,  F01D11/122 ,  F01D11/125 ,  F04D29/023 ,  F04D29/324 ,  B05D5/00 ,  F05D2220/36 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/307 ,  F05D2300/134 ,  F05D2300/43

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

公开(公告)号：US11761094B2

公开(公告)日：2023-09-19

申请号：US17313847

申请日：2021-05-06

Applicant: Applied Materials, Inc.

Inventor： David Britz ,  Pravin K. Narwankar ,  David Thompson ,  Yuriy Melnik ,  Sukti Chatterjee

IPC: F01D5/28 ,  C23C28/00 ,  F01D5/18 ,  C23C16/455 ,  C23C16/52 ,  C23C28/04 ,  C23C16/40 ,  C23C14/08

CPC classification number: C23C28/3455 ,  C23C16/45525 ,  C23C16/52 ,  C23C28/3215 ,  C23C28/345 ,  F01D5/186 ,  F01D5/288 ,  C23C14/083 ,  C23C16/40 ,  C23C28/042 ,  F05D2230/31 ,  F05D2240/24 ,  F05D2260/95 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/134 ,  Y10T428/2462

Abstract: Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof and can have a thickness from 1 nm to 3,000 nm.

公开(公告)号：US20190119804A1

公开(公告)日：2019-04-25

申请号：US16306635

申请日：2017-06-06

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Shuji TANIGAWA ,  Masahiko MEGA ,  Taiji TORIGOE ,  Yoshifumi OKAJIMA ,  Daisuke KUDO

IPC: C23C4/11 ,  C23C4/134 ,  F01D5/28 ,  F01D9/04 ,  F01D25/12

CPC classification number: C23C4/11 ,  C23C4/073 ,  C23C4/134 ,  C23C4/18 ,  F01D5/28 ,  F01D5/286 ,  F01D5/288 ,  F01D9/02 ,  F01D9/041 ,  F01D25/12 ,  F02C7/00 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2260/95 ,  F05D2300/134 ,  F05D2300/20 ,  F05D2300/5023 ,  F05D2300/514 ,  F23R3/42

Abstract: A thermal barrier coating includes a highly porous layer and a dense layer. The highly porous layer is formed on a heat-resistant base, is made of ceramic, has pores, has a layer thickness of equal to or larger than 0.3 mm and equal to or smaller than 1.0 mm, and has a pore ratio of equal to or higher than 1 vol % and equal to or lower than 30 vol %. The dense layer is formed on the highly porous layer, is made of ceramic, has a pore ratio of equal to or lower than 0.9 vol % that is equal to or lower than the pore ratio of the highly porous layer, and has a layer thickness of equal to or smaller than 0.05 mm.

公开(公告)号：US09429029B2

公开(公告)日：2016-08-30

申请号：US13189043

申请日：2011-07-22

Applicant: Enzo Macchia ,  Barry Barnett ,  Andreas Eleftheriou ,  Tom McDonough ,  George Guglielmin ,  Joe Lanzino

Inventor： Enzo Macchia ,  Barry Barnett ,  Andreas Eleftheriou ,  Tom McDonough ,  George Guglielmin ,  Joe Lanzino

IPC: F03B3/12 ,  F01D5/30

CPC classification number: F01D5/3092 ,  F01D5/005 ,  F01D5/28 ,  F05B2230/90 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2260/94 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/13 ,  F05D2300/131 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/134 ,  F05D2300/143 ,  F05D2300/16 ,  F05D2300/1614 ,  F05D2300/1616 ,  F05D2300/609

Abstract: An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.

Abstract translation: 燃气涡轮发动机的翼型叶片包括配置成与配合的转子毂配合连接的根部以及远离根部延伸的翼型件。 根由第一金属组成，并且在其至少一部分上具有由第二金属组成的纳米晶体金属涂层。 还公开了通过将纳米晶体金属涂层施加到叶片根部的一部分来保护这种叶片的方法。

公开(公告)号：US09382164B2

公开(公告)日：2016-07-05

申请号：US13992880

申请日：2011-12-05

Applicant: Anne-Sophie Andreani ,  Francis Rebillat ,  Angeline Poulon ,  Jacques Thebault ,  Anne Sauveroche

Inventor： Anne-Sophie Andreani ,  Francis Rebillat ,  Angeline Poulon ,  Jacques Thebault ,  Anne Sauveroche

IPC: C04B41/50 ,  C04B35/505 ,  C04B35/515 ,  C04B35/56 ,  C04B35/58 ,  C04B35/66 ,  C04B41/00 ,  C04B41/51 ,  C04B41/87 ,  C04B41/88

CPC classification number: C04B35/505 ,  C04B35/515 ,  C04B35/5156 ,  C04B35/5622 ,  C04B35/58078 ,  C04B35/66 ,  C04B41/009 ,  C04B41/5057 ,  C04B41/5133 ,  C04B41/87 ,  C04B41/88 ,  C04B2235/3804 ,  C04B2235/3813 ,  C04B2235/3839 ,  C04B2235/3852 ,  C04B2235/666 ,  C04B2235/728 ,  C04B2235/9684 ,  F05D2300/123 ,  F05D2300/134 ,  F05D2300/135 ,  F05D2300/15 ,  Y10T428/30 ,  C04B35/83 ,  C04B41/4545 ,  C04B41/507

Abstract: A refractory material that can withstand high temperatures in an oxidizing medium and containing at least: a first constituent corresponding to hafnium, or to a non-oxide compound of hafnium, or circular in a or a non-oxide compound of zirconium, or corresponding to a mixture of at least two metals and/or compounds selected from hafnium a non-oxide compound of hafnium, zirconium, and a non-oxide compound of zirconium; a second constituent corresponding to the boron or to a non-oxide compound of boron, or corresponding to a mixture of boron and a non-oxide compound of boron; and a third constituent corresponding to a rare earth RE or to a non-oxide compound of the rare earth RE, or corresponding to a mixture of rare earth RE and a non-oxide compound of the rare earth RE, where RE is selected from scandium, yttrium, and the lanthanides. The material contains neither silicon nor a compound of silicon.

Abstract translation: 一种耐火材料，其能够承受氧化介质中的高温，并且至少包含：对应于铪的第一组分，或铪的非氧化物化合物，或在锆的非氧化物化合物中的圆形或对应于 至少两种金属和/或选自铪，铪，锆的非氧化物化合物和锆的非氧化物化合物的化合物的混合物; 对应于硼或与硼的非氧化物化合物相对应的第二组分，或对应于硼和硼的非氧化物化合物的混合物; 对应于稀土RE的稀土RE或非稀土RE的非氧化物化合物的第三成分，或稀土RE与稀土RE的非氧化物的混合物，其中RE选自钪 ，钇和镧系元素。 该材料既不含硅也不含硅化合物。

公开(公告)号：US20110299996A1

公开(公告)日：2011-12-08

申请号：US13202260

申请日：2010-01-30

Applicant: Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling

Inventor： Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling

IPC: F01D5/14 ,  C23F13/06 ,  B05D1/18 ,  C23C4/12 ,  B05D5/00 ,  B05D1/02 ,  C23F13/00 ,  C23C16/44

CPC classification number: F01D9/04 ,  C23C28/321 ,  C23C28/322 ,  C23C28/34 ,  C23C28/341 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/36 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/314 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/134 ,  F05D2300/161 ,  F05D2300/21 ,  F05D2300/222 ,  F05D2300/226 ,  F05D2300/228 ,  F05D2300/48 ,  Y02T50/67 ,  Y02T50/6765

Abstract: A gas turbine component and a method for producing an anti-erosion coating system are disclosed. The gas turbine component includes a basic material, on which an anti-erosion coating system is provided that is a multilayer system including at least one ductile metal layer and at least one hard, ceramics-containing layer for forming a partial anti-erosion system. At least one anti-corrosion layer that has a lower electrochemical potential than the basic material is provided between the partial anti-erosion system and the basic material, thus providing cathodic corrosion protection.

Abstract translation: 公开了一种燃气轮机部件及其制造方法。 燃气轮机部件包括基材，其上设置有防腐蚀涂层系统，其是包括至少一个延性金属层和至少一个用于形成部分抗侵蚀系统的含硬陶瓷的层的多层系统。 在部分抗侵蚀系统和基础材料之间提供至少一个具有比基本材料更低的电化学电位的防腐蚀层，从而提供阴极腐蚀保护。

公开(公告)号：US07229705B1

公开(公告)日：2007-06-12

申请号：US11465288

申请日：2006-08-17

Applicant: Mary B. Johnson, legal representative ,  Robert W. Bruce

Inventor： Lyman A. Johnson, deceased

IPC: B32B9/00 ,  F03B3/12

CPC classification number: F01D5/288 ,  C23C14/08 ,  C23C14/24 ,  C23C28/321 ,  C23C28/325 ,  C23C28/3455 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2300/134 ,  F05D2300/15 ,  F05D2300/611 ,  Y10T428/12549 ,  Y10T428/12771 ,  Y10T428/12806

Abstract: The present invention is a turbine engine component comprising a superalloy substrate, a bond coat overlying the substrate having a thickness in the range of about 0.0005 inch to about 0.005 inch, a thin alumina scale overlying the bond coat, and a thermal barrier coating (TBC) overlying the thin alumina scale, the TBC having a thickness in the range of about 0.0025 inch to about 0.010 inch, and comprising at least mischmetal oxide.

Abstract translation: 本发明是一种涡轮发动机部件，其包括超合金基板，覆盖在基板上的粘合涂层，其厚度在约0.0005英寸至约0.005英寸的范围内，覆盖在粘合涂层上的薄氧化铝标尺，以及热障涂层 ），所述TBC的厚度在约0.0025英寸至约0.010英寸的范围内，并且至少包含混合稀土氧化物。

公开(公告)号：US20050196635A1

公开(公告)日：2005-09-08

申请号：US10792161

申请日：2004-03-03

Applicant: Lyman Johnson ,  Robert Bruce ,  Mary Johnson

Inventor： Lyman Johnson ,  Robert Bruce ,  Mary Johnson

IPC: B32B9/00

CPC classification number: F01D5/288 ,  C23C14/08 ,  C23C14/24 ,  C23C28/321 ,  C23C28/325 ,  C23C28/3455 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2300/134 ,  F05D2300/15 ,  F05D2300/611 ,  Y10T428/12549 ,  Y10T428/12771 ,  Y10T428/12806

Abstract: The present invention is a turbine engine component comprising a superalloy substrate, a bond coat overlying the substrate having a thickness in the range of about 0.0005 inch to about 0.005 inch, a thin alumina scale overlying the bond coat, and a thermal barrier coating (TBC) overlying the thin alumina scale, the TBC having a thickness in the range of about 0.0025 inch to about 0.010 inch, and comprising at least mischmetal oxide. The present invention is also a method for the application of a thermal barrier coating to a superalloy turbine engine component comprising the steps of: providing an electron beam physical vapor deposition apparatus, providing a turbine engine component comprising a surface to be coated, providing an oxide ingot comprising mischmetal oxide and another oxide material selected from the group consisting of yttria-stablized zirconia, zirconia, yttria, hafnia, at least one other rare earth oxide, and combinations thereof, placing the component and the ingot into the apparatus, drawing a vacuum within the apparatus, forming a melt pool on the ingot, dispersing mischmetal oxide vapors and yttria-stabilized zirconia vapors, depositing the mischmetal oxide vapors and the yttria-stabilized zirconia vapors onto the surface to be coated, said deposition forming a thermal barrier coating having a thickness in the range of about 0.0025 inch to about 0.010 inch.

Abstract translation: 本发明是一种涡轮发动机部件，其包括超合金基板，覆盖在基板上的粘合涂层，其厚度在约0.0005英寸至约0.005英寸的范围内，覆盖在粘合涂层上的薄氧化铝标尺和热障涂层（TBC ），所述TBC的厚度在约0.0025英寸至约0.010英寸的范围内，并且至少包含混合稀土氧化物。 本发明也是一种将热障涂层应用于超级合金涡轮发动机部件的方法，包括以下步骤：提供电子束物理气相沉积装置，提供包括待涂覆表面的涡轮发动机部件，提供氧化物 铸锭包括混合氧化物和选自氧化钇稳定氧化锆，氧化锆，氧化钇，铪，至少一种其他稀土氧化物的其它氧化物材料及其组合，将组分和锭放入设备中，抽真空 在所述装置内，在所述锭上形成熔池，分散混合氧化物蒸气和氧化钇稳定的氧化锆蒸汽，将所述混合氧化物蒸气和所述氧化钇稳定的氧化锆蒸气沉积在待涂覆的表面上，所述沉积形成具有 厚度在约0.0025英寸至约0.010英寸的范围内。

公开(公告)号：US20030224200A1

公开(公告)日：2003-12-04

申请号：US10063962

申请日：2002-05-30

Applicant: General Electric Company

Inventor： Robert William Bruce

IPC: B32B015/04 ,  F03B003/12

CPC classification number: C23C28/321 ,  C23C14/083 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/288 ,  F05C2201/0469 ,  F05D2230/90 ,  F05D2300/134 ,  F05D2300/15 ,  F05D2300/611 ,  Y10T428/12611 ,  Y10T428/12944

Abstract: A coating material, particularly a thermal barrier coating, for a component intended for use in a hostile environment, such as the superalloy turbine, combustor and augmentor components of a gas turbine engine. The coating material is zirconia that is partially stabilized with yttria and to which lanthana, neodymia and/or tantala are alloyed to increase the impact resistance of the coating.

Abstract translation: 用于在恶劣环境中使用的组分的涂层材料，特别是热障涂层，例如燃气轮机的超级合金涡轮机，燃烧器和增压器部件。 涂层材料是用氧化钇部分稳定的氧化锆，并且将氧化镧，钕和/或钽酸铝合金化以增加涂层的耐冲击性。

公开(公告)号：US20170081753A1

公开(公告)日：2017-03-23

申请号：US14859587

申请日：2015-09-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Liming ZHANG ,  Christopher Edward THOMPSON ,  James Ryan CONNOR ,  John D. WARD ,  Michael Anthony DEPALMA

IPC: C23C4/134 ,  F01D5/28 ,  F23R3/00 ,  C23C14/22

CPC classification number: C23C4/134 ,  C23C10/18 ,  C23C10/20 ,  C23C10/30 ,  C23C10/60 ,  C23C14/221 ,  C23C28/321 ,  C23C28/3455 ,  F01D5/288 ,  F05D2300/134 ,  F23R3/002

Abstract: A process for forming a thermal barrier coating system on a substrate is disclosed including preparing a slurry including a donor powder, an activator powder, and a binder. The donor powder includes a metallic aluminum alloy having a melting temperature higher than aluminum, and the binder includes at least one organic polymer gel. The process further includes applying the slurry to the substrate, heating the slurry to form an aluminide bond coating including an additive aluminide layer and an aluminide interdiffusion zone disposed between the substrate and the additive aluminide layer, and applying a thermal barrier coating to the aluminide bond coating. The thermal barrier coating may be a dense vertically-cracked thermal barrier coating, and the substrate may be a gas turbine component. Thermal barrier coating systems formed by the process are also disclosed.