公开(公告)号：US20140137408A1

公开(公告)日：2014-05-22

申请号：US13678763

申请日：2012-11-16

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ronald Scott Bunker ,  John Wesley Harris, JR.

IPC: F01D25/12

CPC classification number: F01D5/186 ,  F01D5/288 ,  F05D2230/14 ,  F05D2230/312 ,  F05D2230/313 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T29/4932

Abstract: In one aspect, a method of forming a hot gas path component is provided. The method includes forming at least one groove in an outer surface of a substrate, wherein the at least one groove has a base and a top. The method further includes filling the at least one groove with a filler. The method also includes applying at least one cover layer over at least a portion of the outer surface of the substrate such that the at least one groove and the at least one cover layer define at least one micro-channel for cooling the component. The filler is automatically removed from the at least one micro-channel during application of the at least one cover layer. Methods for coating a hot gas component and for assembling a turbine engine assembly are also provided.

Abstract translation: 一方面，提供了形成热气路径部件的方法。 该方法包括在基底的外表面中形成至少一个凹槽，其中所述至少一个凹槽具有基底和顶部。 该方法还包括用填料填充至少一个凹槽。 该方法还包括在衬底的外表面的至少一部分上施加至少一个覆盖层，使得至少一个沟槽和至少一个覆盖层限定至少一个用于冷却部件的微通道。 在施加至少一个覆盖层期间，填料自动从至少一个微通道移除。 还提供了用于涂覆热气体组分和组装涡轮发动机组件的方法。

公开(公告)号：US20160040537A1

公开(公告)日：2016-02-11

申请号：US14453914

申请日：2014-08-07

Applicant: General Electric Company

Inventor： David Randolph Spracher ,  Kevin Leon Bruce ,  John Wesley Harris, JR. ,  Brian Denver Potter ,  William Scott Zemitis

IPC: F01D5/22

CPC classification number: F01D5/225 ,  F01D5/147 ,  Y02T50/673

Abstract: A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil.

Abstract translation: 用于涡轮叶片的中跨护罩组件包括限定翼梁窝和紧固件孔的压力侧护罩主体和限定翼梁窝和紧固件孔的吸力侧护罩主体。 中跨护罩组件还包括翼梁，翼梁具有在压力侧护罩主体的翼梁槽内延伸的第一端部和在吸力侧护罩主体的翼梁槽内延伸的第二端部。 翼梁形成为延伸穿过涡轮机叶片的钻孔。 紧固件形成为延伸穿过压力侧护罩主体的紧固件孔，涡轮叶片的紧固件孔口和吸力侧护罩主体的紧固件孔，以提供夹紧力以将压力侧和吸力侧护罩体抵靠 机翼。

公开(公告)号：US20140170433A1

公开(公告)日：2014-06-19

申请号：US13719772

申请日：2012-12-19

Applicant: GENERAL ELECTRIC COMPANY

Inventor： David Edward Schick ,  Srikanth Chandrudu Kottilingam ,  Benjamin Paul Lacy ,  John Wesley Harris, JR.

IPC: B22F7/08

CPC classification number: B22F7/08 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B23P2700/06 ,  C22C1/0433 ,  F01D5/187 ,  F05D2230/22 ,  F05D2260/204 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T428/12028 ,  Y10T428/24744

Abstract: Methods for providing a near-surface cooling microchannel in a component include forming a near-surface cooling microchannel in a first surface of a pre-sintered preform, disposing the first surface of the pre-sintered preform onto an outer surface of the base article such that an opening of the outer surface of the base article is aligned with the near-surface cooling microchannel in the first surface of the pre-sintered preform, and, heating the pre-sintered preform to bond it to the base article, wherein the opening of the outer surface of the base article remains aligned with the near-surface cooling microchannel in the first surface of the pre-sintered preform.

Abstract translation: 在组件中提供近表面冷却微通道的方法包括在预烧结预型件的第一表面中形成近表面冷却微通道，将预烧结预制件的第一表面设置在基底制品的外表面上， 基底制品的外表面的开口与预烧结预型件的第一表面中的近表面冷却微通道对准，并且加热预烧结的预成型件以将其粘合到基底制品上，其中开口 基底制品的外表面与预烧结预制件的第一表面中的近表面冷却微通道保持一致。

公开(公告)号：US20150044059A1

公开(公告)日：2015-02-12

申请号：US13963322

申请日：2013-08-09

Applicant: General Electric Company

Inventor： Stephen Paul Wassynger ,  John Wesley Harris, JR. ,  Michael James Healy

IPC: F01D5/14 ,  F01D5/00

CPC classification number: F01D5/147 ,  F01D5/005 ,  F01D5/186 ,  F01D5/187 ,  F05D2230/22 ,  F05D2240/122 ,  F05D2240/304 ,  Y10T29/49318

Abstract: An airfoil includes a main portion formed of a base material. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising at least one pre-sintered preform (PSP) material operatively coupled to the base material proximate the trailing edge region.

Abstract translation: 机翼包括由基材形成的主体部。 还包括主要部分的后缘区域。 还包括后缘补充结构，其包括至少一个可操作地连接到靠近后缘区域的基底材料的预烧结预成型件（PSP）材料。

公开(公告)号：US20190040755A1

公开(公告)日：2019-02-07

申请号：US15667771

申请日：2017-08-03

Applicant: General Electric Company

Inventor： William Scott ZEMITIS ,  Martin JASPER ,  Brad VAN TASSEL ,  John Wesley Harris, JR. ,  Thomas James Brunt

IPC: F01D9/04

CPC classification number: F01D9/047 ,  F01D9/041 ,  F01D9/065 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2260/941

Abstract: A turbine nozzle segment includes a radially-inner endwall, a radially-outer endwall, and a pair of airfoil-shaped vanes extending between the radially-inner endwall and the radially-outer endwall. The back face of the radially-inner endwall and/or the back face of the radially-outer endwall has a pocket formed therein in an area between the pressure sidewall of the first vane and the suction sidewall of the second vane to enhance stiffness distribution between the second vane and the radially-inner endwall and/or radially-outer endwall.

公开(公告)号：US20160040535A1

公开(公告)日：2016-02-11

申请号：US14453924

申请日：2014-08-07

Applicant: General Electric Company

Inventor： David Randolph Spracher ,  Kevin Leon Bruce ,  John Wesley Harris, JR. ,  Daryl R. Collins ,  William Scott Zemitis

IPC: F01D5/22

CPC classification number: F01D5/22 ,  F01D5/147 ,  F01D5/225 ,  Y02T50/671 ,  Y02T50/673

Abstract: A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade.

Abstract translation: 用于涡轮叶片翼型件的中跨护罩组件包括与翼型件的压力侧壁相关联的压力侧护罩主体和与翼型件的吸力侧壁相关联的抽吸侧护罩主体。 压力侧护罩主体和吸力侧护罩主体中的至少一个限定了联接翼梁，其形成为至少部分地延伸穿过限定在涡轮叶片的翼型内的钻孔。

公开(公告)号：US20150184517A1

公开(公告)日：2015-07-02

申请号：US14038076

申请日：2013-09-26

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith ,  John Wesley Harris, JR.

IPC: F01D5/18 ,  B26F1/26 ,  F01D5/14 ,  B23H9/14

CPC classification number: F01D5/186 ,  B23H9/14 ,  B23K26/389 ,  B26F1/26 ,  F01D5/141 ,  F01D5/187 ,  F05D2230/10 ,  F05D2230/12 ,  Y02T50/676

Abstract: A method for fabricating an airfoil includes forming a diffuser section in an exterior surface of the airfoil. The diffuser section is defined by at least an outer surface and an inner surface that converge at a stop surface. The method also includes positioning a drilling element of a drilling device on the stop surface. The method further includes orienting the drilling element at a first angle relative to the exterior surface. The method also includes forming, using the drilling element, a cooling channel extending through the airfoil from the stop surface to an interior surface, thereby forming the cooling channel at substantially the first angle.

Abstract translation: 一种用于制造翼型的方法包括在翼型件的外表面中形成扩散器部分。 扩散器部分由至少外表面和在止动表面处会聚的内表面限定。 该方法还包括将钻井装置的钻孔元件定位在止动表面上。 该方法还包括相对于外表面以第一角度定向钻孔元件。 该方法还包括使用钻孔元件形成从止动表面延伸穿过翼型件到内表面的冷却通道，从而以大致第一角度形成冷却通道。