公开(公告)号：US20180372416A1

公开(公告)日：2018-12-27

申请号：US15633169

申请日：2017-06-26

Applicant: United Technologies Corporation

Inventor： Chris Vargas ,  Daniel B. Denis

IPC: F28D9/00 ,  B23P15/26 ,  B21D53/04 ,  F28F9/02 ,  F01D25/08

CPC classification number: F28D9/0093 ,  B21D53/04 ,  B23P15/26 ,  F01D25/08 ,  F05D2220/32 ,  F05D2230/311 ,  F28D1/0308 ,  F28D1/05366 ,  F28D9/0031 ,  F28F1/16 ,  F28F1/26 ,  F28F1/42 ,  F28F1/422 ,  F28F9/02

Abstract: A method is provided for manufacturing at least a portion of a heat exchanger. During this method, a first heat exchanger section is formed that includes a base and a plurality of protrusions. The forming of the first heat exchanger section includes building up at least one protrusion material on the base to form the protrusions. The first heat exchanger section is attached to a second heat exchanger section. A plurality of flow channels are defined between the first heat exchanger section and the second heat exchanger section.

公开(公告)号：US20170362952A1

公开(公告)日：2017-12-21

申请号：US15616545

申请日：2017-06-07

Applicant: United Technologies Corporation

Inventor： Pantcho Stoyanov ,  Christopher W. Strock ,  Agnieszka M. Wusatowska-Sarnek

IPC: F01D11/12 ,  F01D25/24 ,  F01D5/02 ,  F01D21/00

CPC classification number: F01D11/122 ,  F01D5/02 ,  F01D11/001 ,  F01D21/003 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2260/80 ,  F05D2300/516 ,  Y02T50/672

Abstract: An embodiment of a gas turbine engine component includes an abrasive coating disposed on at least a portion of a sealing region. The abrasive coating includes an inner abrasive region disposed outward of the sealing region in a coating thickness direction, and an outer abrasive region disposed outward of the inner abrasive region in the coating thickness direction. The inner abrasive region includes abrasive particles retained in an inner matrix, and the outer abrasive region includes abrasive particles retained in an outer matrix. At least one of the inner matrix and the outer matrix is modified with a first indicator material. At least one aspect of the first indicator material corresponds to a thickness range of the abrasive coating being within the inner thickness region or the outer thickness region.

公开(公告)号：US20170297054A1

公开(公告)日：2017-10-19

申请号：US15515677

申请日：2015-12-03

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Taiji TORIGOE ,  Masahiko MEGA ,  Yoshifumi OKAJIMA ,  Shuji TANIGAWA ,  Masamitsu KUWABARA ,  Naotoshi OKAYA

IPC: B05D1/32 ,  F01D9/04 ,  C23C26/00 ,  B05D7/14 ,  B05D1/02 ,  F01D5/28 ,  F23R3/00 ,  B05D3/06

CPC classification number: B05D1/32 ,  B05D1/02 ,  B05D3/062 ,  B05D7/14 ,  C23C4/02 ,  C23C4/18 ,  C23C26/00 ,  F01D5/186 ,  F01D5/284 ,  F01D5/288 ,  F01D9/04 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2300/20 ,  F05D2300/44 ,  F05D2300/611 ,  F23R3/002 ,  Y02T50/676

Abstract: A method of forming a sprayed coating includes preparing a spray target member having a surface on which openings of first ends of holes are formed, preparing a plurality of masking pins each of which comprises metal, and inserting each of the masking pins into a corresponding one of the holes so that each of the masking pins partially protrudes from the surface. The method also includes applying an adhesive agent for fixing the masking pins to the respective holes, to at least one of the holes or the masking pins, forming a ceramic layer by spraying on the surface of the spraying target member, the ceramic layer comprising a ceramic material, while the masking pins are fixed to the respective holes via the adhesive agent, and removing the masking pins from the holes after the spraying step.

公开(公告)号：US20170226621A1

公开(公告)日：2017-08-10

申请号：US15425451

申请日：2017-02-06

Applicant: MTU Aero Engines AG

Inventor： Philipp DOEBBER ,  Frank SEIDEL

IPC: C23C4/12 ,  F01D5/28 ,  F01D9/02 ,  C23C14/22

CPC classification number: C23C4/12 ,  C23C4/11 ,  C23C4/18 ,  C23C14/221 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/288 ,  F01D9/02 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2300/222 ,  F05D2300/514 ,  Y02T50/6765

Abstract: Disclosed is a thermal barrier coating system for components of a turbomachine, especially for high temperature-stressed or hot gas-stressed components of a turbomachine, comprising a ceramic coating of fully or partially stabilized zirconium oxide, and an oxide cover coating which comprises aluminum and at least one element from the group lanthanum, magnesium, silicon, calcium and sodium. The aluminum oxide exists at least partially as free α-Al2O3. Also disclosed is a method for producing a corresponding thermal barrier coating system.

公开(公告)号：US20160369637A1

公开(公告)日：2016-12-22

申请号：US15121513

申请日：2015-02-18

Applicant: Siemens Aktiengesellschaft

Inventor： Ramesh SUBRAMANIAN ,  Stefan LAMENSCHERF ,  Cora SCHILLIG ,  Neil HITCHMAN ,  Dimitrios ZOIS

IPC: F01D5/28 ,  C23C16/22 ,  C23C4/134 ,  F01D9/04 ,  F01D9/02

CPC classification number: F01D5/187 ,  C23C4/02 ,  C23C4/134 ,  C23C16/22 ,  F01D5/286 ,  F01D5/288 ,  F01D9/023 ,  F01D9/041 ,  F01D11/122 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2250/13 ,  F05D2250/28 ,  F05D2260/202 ,  F05D2300/10 ,  F05D2300/5023 ,  F05D2300/611

Abstract: Thermal barrier coatings (TBCs) for turbine engine components are applied over engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC. The ESFs help anchor the TBC layer and/or localize cracks that are bounded by one or more of the ESFs. During engine operation the ESFs arrest thermal stress-or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. In some embodiments, the ESFs are combined with engineered groove features that are formed in the TBC.

Abstract translation: 用于涡轮发动机部件的热障涂层（TBC）应用于在组件衬底中形成的工程表面特征（ESF）上，或者施加在衬底和TBC之间的中间层内。 ESFs帮助锚定TBC层和/或定位由一个或多个ESF界定的裂缝。 在发动机运行期间，ESF阻止了TBC内的热应力或异物损伤（FOD）引起的裂纹扩展，否则可能会导致TBC的过度剥落和随后对基底下的涡轮部件的热暴露损坏。 在一些实施例中，ESF与在TBC中形成的工程化凹槽特征组合。

公开(公告)号：US09429025B2

公开(公告)日：2016-08-30

申请号：US13805694

申请日：2011-04-21

Applicant: William C. Harris, Jr. ,  John P. Kopchik ,  Richard Ely

Inventor： William C. Harris, Jr. ,  John P. Kopchik ,  Richard Ely

IPC: F01D5/14 ,  B64C27/46 ,  F01D5/28 ,  B64C11/20 ,  B64C27/473

CPC classification number: F01D5/147 ,  B64C11/205 ,  B64C27/463 ,  B64C27/473 ,  F01D5/286 ,  F01D5/288 ,  F05D2230/311 ,  F05D2230/90 ,  F05D2300/611

Abstract: A rotor blade including a main portion having a main portion leading edge shield; a main portion impact-resistant layer formed on a nose of the leading edge shield; a main portion erosion-resistant layer formed on a top and bottom of the main portion, rearward of the main portion impact-resistant layer; a main portion foil formed on the top and the bottom of the main portion rearward of the main portion erosion-resistant layer; a tip cap having a tip cap leading edge shield; a tip cap impact-resistant layer formed on a surface of the tip cap leading edge shield; and a tip cap foil formed on the top and the bottom of the tip cap rearward of the tip cap erosion-resistant layer.

Abstract translation: 一种转子叶片，包括具有主要部分前缘屏蔽的主要部分; 形成在前缘护罩的鼻部上的主要部分抗冲击层; 主要部分抗侵蚀层，形成在主体部分的顶部和底部上，在主体部分耐冲击层的后面; 主要部分箔形成在主体部分耐腐蚀层后面的主体部分的顶部和底部上; 具有顶盖前缘屏蔽的末端盖; 顶盖耐冲击层，形成在尖端盖前缘屏蔽的表面上; 以及在顶盖耐腐蚀层的后方形成在顶盖的顶部和底部上的尖端盖箔。

公开(公告)号：US09404185B2

公开(公告)日：2016-08-02

申请号：US14467938

申请日：2014-08-25

Applicant: HERAKLES ,  SNECMA

Inventor： Eric Bouillon ,  Nicolas Eberling-Fux ,  Serge Chateigner

IPC: C23C18/12 ,  C03C3/087 ,  C03C8/00 ,  C04B41/00 ,  C04B41/50 ,  C04B41/52 ,  C04B41/86 ,  C04B41/89 ,  F01D5/28 ,  C23C4/10

CPC classification number: C23C18/1216 ,  C03C3/087 ,  C03C8/00 ,  C04B41/009 ,  C04B41/5022 ,  C04B41/52 ,  C04B41/86 ,  C04B41/89 ,  C23C4/11 ,  F01D5/282 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T428/249924 ,  C04B41/4539 ,  C04B41/4554 ,  C04B41/5059 ,  C04B41/4527 ,  C04B41/522 ,  C04B35/565 ,  C04B35/806

Abstract: A method of smoothing the surface of a ceramic matrix composite material part that presents a surface that is undulating and rough. The method includes depositing a refractory vitreous coating on the surface of the part, the vitreous coating essentially containing silica, alumina, baryte, and lime.

Abstract translation: 使陶瓷基复合材料部件的表面平滑化的方法，该陶瓷基复合材料部件具有起伏和粗糙的表面。 该方法包括在部件的表面上沉积耐火玻璃质涂层，玻璃质涂层基本上含有二氧化硅，氧化铝，重晶石和石灰。

公开(公告)号：US20150354371A1

公开(公告)日：2015-12-10

申请号：US14762062

申请日：2014-02-12

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Tomomi SONOO

IPC: F01D5/18 ,  F01D5/28 ,  B24B19/14

CPC classification number: F01D5/186 ,  B23P6/002 ,  B23P2700/06 ,  B24B1/04 ,  B24B19/14 ,  C23C4/18 ,  F01D5/005 ,  F01D5/288 ,  F05D2220/30 ,  F05D2230/10 ,  F05D2230/311 ,  F05D2230/90 ,  F05D2260/202

Abstract: Provided are a turbine blade machining method and a machining tool, which allow efficient machining of a through-hole running from the surface of a turbine blade to the interior thereof, and a turbine blade. This turbine blade machining method, whereby a through-hole is machined in a turbine blade with a protective film formed on a surface of a substrate, has: an insertion step of inserting a machining tool, including a grinding region provided at a tip thereof, into the through-hole with such an orientation that the grinding region faces the surface of the through-hole; and a removal step of grinding the protective film laminated in the through-hole with the grinding region of the machining tool inserted into the through-hole, to remove the protective film laminated in the through-hole.

Abstract translation: 提供了一种涡轮机叶片加工方法和加工工具，其允许从涡轮叶片的表面到其内部的通孔的高效加工，以及涡轮叶片。 这种涡轮机叶片加工方法，其中在涡轮叶片中加工有形成在基板表面上的保护膜的通孔具有：插入步骤，插入包括设置在其顶端的研磨区域的加工工具， 以使研磨区域朝向通孔表面的方向进入通孔; 以及通过插入到通孔中的加工工具的研磨区域来研磨层叠在通孔中的保护膜的去除步骤，以去除层压在通孔中的保护膜。

公开(公告)号：US09151175B2

公开(公告)日：2015-10-06

申请号：US14188958

申请日：2014-02-25

Applicant: Siemens Aktiengesellschaft

Inventor： Kok-Mun Tham ,  Vincent P. Laurello ,  Ching-Pang Lee ,  Gm Salam Azad ,  Nicholas F. Martin, Jr. ,  David G. Sansom ,  Neil Hitchman

IPC: F01D11/12

CPC classification number: F01D5/187 ,  C23C4/02 ,  C23C4/134 ,  C23C16/22 ,  F01D5/286 ,  F01D5/288 ,  F01D9/023 ,  F01D9/041 ,  F01D11/122 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2250/13 ,  F05D2250/28 ,  F05D2260/202 ,  F05D2300/10 ,  F05D2300/5023 ,  F05D2300/611

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting alternating rows of first and second height ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. The first ridges have a first ridge height greater than that of the second ridges. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, at and below the second ridge height, optimizes engine airflow characteristics, while the upper zone, between tips of the second and first ridges, is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.

Abstract translation: 用于涡轮发动机的涡轮机和压缩机壳体可磨损部件实施例，其具有平面状图案中的复合凹槽和垂直突出的第一和第二高度脊的交替排，以减少，重定向和/或阻挡下游进入凹槽的叶片尖端气流泄漏，而不是涡轮叶片 翼型高低压侧。 第一脊具有大于第二脊的第一脊高度。 这些脊或肋实施例具有第一下和第二上磨损区。 在第二脊高处和下方的下部区域优化发动机气流特性，同时优化第二和第二脊部的尖端之间的上部区域，以通过比下部区域更容易磨损来最小化叶片尖端间隙和磨损。

公开(公告)号：US20150030459A1

公开(公告)日：2015-01-29

申请号：US14373651

申请日：2012-11-07

Applicant: Siemens Aktiengesellschaft

Inventor： Jorg Schurhoff

IPC: F01D5/28 ,  C23C30/00

CPC classification number: F01D25/24 ,  C23C4/06 ,  C23C4/08 ,  C23C14/00 ,  C23C24/04 ,  C23C30/005 ,  F01D25/243 ,  F01D25/265 ,  F04D29/023 ,  F04D29/083 ,  F04D29/403 ,  F05D2230/311 ,  F05D2230/313 ,  F05D2230/314 ,  F05D2230/90 ,  F05D2240/55 ,  F05D2300/132 ,  F05D2300/17 ,  F05D2300/22 ,  F16L9/22

Abstract: A turbomachine component is provided having at least two sub-components that are separated by a parting joint and each have a sealing surface at the parting joint, at least one of the two sealing surfaces being convex in order to form a linear contact of the two sealing surfaces. At least one of the sealing surfaces has a coating on it which includes a hard material, is a maximum of 30 μm thick and is applied using a vapour deposition method, or a coating which includes a chrome-containing alloy, is a maximum of 30 μm thick and is applied by a vapour deposition method, or is a maximum of 300 μm thick and applied using a thermal spraying method.

Abstract translation: 提供了一种涡轮机组件，其具有由分离接头分开的至少两个子部件，并且每个在分离接头处具有密封表面，两个密封表面中的至少一个是凸形的，以形成两者的线性接触 密封面。 密封面中的至少一个在其上具有包括硬质材料的涂层，其最大厚度为30μm，并且使用气相沉积法施加，或包括含铬合金的涂层最多为30 通过气相沉积法施加，或最大厚度为300μm，并使用热喷涂法施加。