公开(公告)号：EP2867471A4

公开(公告)日：2015-08-26

申请号：EP13832864

申请日：2013-06-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  BERGMAN RUSSELL J

IPC: F01D9/04

CPC classification number: F01D25/12 ,  F01D9/02 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

公开(公告)号：EP3181819A1

公开(公告)日：2017-06-21

申请号：EP16202770

申请日：2016-12-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  KOHLI ATUL

IPC: F01D5/18

CPC classification number: F01D5/189 ,  F01D5/188 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/22141 ,  F23R3/002

Abstract: A baffle insert (32) for a component of a gas turbine engine is provided. The baffle insert having: a plurality of trip strips (40) extending upwardly from an exterior surface (38) of the baffle insert; and at least one rib (42) extending upwardly from the exterior surface of the baffle insert.

Abstract translation: 提供了用于燃气涡轮发动机的部件的挡板插件（32）。 挡板插入件具有：多个从挡板插入件的外表面（38）向上延伸的脱扣条（40） 和至少一个从挡板插件的外表面向上延伸的肋（42）。

公开(公告)号：EP3105437A4

公开(公告)日：2017-03-15

申请号：EP15748506

申请日：2015-01-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  KOHLI ATUL

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/06

CPC classification number: F01D9/065 ,  F01D5/188 ,  F01D5/189 ,  F05D2240/127 ,  F05D2260/201 ,  F05D2260/2212 ,  Y02T50/676

Abstract: An engine component assembly includes at least one cavity that is in communication with a source of cooling air. An insert disposed within the cavity includes a plurality of scoops protruding into a flow of cooling air for directing cooling air through the insert and against an inner surface of the cavity.

Abstract translation: 发动机部件组件包括至少一个与冷却空气源连通的空腔。 设置在空腔内的插入件包括多个突出到冷却空气流中的勺，用于引导冷却空气穿过插入件并抵靠空腔的内表面。

公开(公告)号：EP2986760A4

公开(公告)日：2017-02-22

申请号：EP14813859

申请日：2014-04-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCBRIEN JOHN ,  CASTLE LEA KENNARD ,  SPANGLER BRANDON W ,  XU JINQUAN

IPC: C30B29/52 ,  B22F3/105 ,  B22F5/04 ,  C30B11/00 ,  C30B21/00 ,  C30B21/02

CPC classification number: F01D5/28 ,  B22C7/02 ,  B22C9/02 ,  B22C9/043 ,  B22C9/061 ,  B22C9/10 ,  B22C9/101 ,  B22C9/108 ,  B22C9/22 ,  B22C9/24 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04 ,  B22D27/045 ,  B22F3/1055 ,  B22F3/11 ,  B22F3/24 ,  B22F5/04 ,  B22F2003/248 ,  B22F2998/00 ,  B22F2998/10 ,  B23K15/0006 ,  B23K15/0086 ,  B23K26/342 ,  B32B1/08 ,  B32B3/08 ,  B32B3/26 ,  B32B5/16 ,  B32B9/005 ,  B32B2250/03 ,  B32B2264/105 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B29/52 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/282 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/175 ,  F05D2300/211 ,  F05D2300/607 ,  F23R3/28 ,  Y02P10/292 ,  Y02P10/295 ,  B22F2003/242 ,  C30B11/14

Abstract: A method of forming a metal single crystal turbine component (10) with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core (20) and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

公开(公告)号：EP3084137A4

公开(公告)日：2017-01-25

申请号：EP14887328

申请日：2014-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHAKKA PITCHAIAH VIJAY ,  AGGARWALA ANDREW S ,  PRAISNER THOMAS J ,  SPANGLER BRANDON W

IPC: F01D5/14

CPC classification number: F01D25/12 ,  F01D5/12 ,  F01D5/145 ,  F01D9/02 ,  F02C3/04 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

公开(公告)号：EP3004597A4

公开(公告)日：2017-01-18

申请号：EP14836289

申请日：2014-05-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  MONGILLO DOMINIC J

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/02 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.

公开(公告)号：EP2971543A4

公开(公告)日：2017-01-11

申请号：EP14767968

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MONGILLO DOMINIC J ,  SPANGLER BRANDON W

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12

CPC classification number: F02C7/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F01D25/30 ,  F02C7/25 ,  F02K1/822 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/127 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2250/141 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/2212 ,  Y02T50/675

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall, a second wall and at least one row of shaped pedestals extending between the first wall and the second wall. The at least one row of shaped pedestals includes a first set of C-shaped pedestals and a second set of C-shaped pedestals adjacent to the first set of C-shaped pedestals.

Abstract translation: 根据本公开的示例性方面的部件包括在第一壁和第二壁之间延伸的第一壁，第二壁和至少一排成形基座。 所述至少一排成形基座包括第一组C形基座和与第一组C形基座相邻的第二组C形基座。

公开(公告)号：EP2959130A4

公开(公告)日：2016-11-02

申请号：EP14753508

申请日：2014-02-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W

IPC: F02C7/12 ,  F01D5/08 ,  F01D25/12

CPC classification number: F01D5/187 ,  B22C7/06 ,  B22C9/103 ,  F01D5/284 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/81 ,  F05D2250/11 ,  F05D2250/185 ,  F05D2260/20 ,  F05D2300/20 ,  Y02T50/676

Abstract: A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.

Abstract translation: 燃气涡轮发动机叶片包括布置在根部和翼型之间的平台。 冷却通道从根部延伸穿过平台到翼型。 冷却通道包括分开到布置在平台中的平台通道中彼此重新接合的第一和第二分支的入口。 翼型通道从平台通道延伸并布置在平台中。

公开(公告)号：EP3047106A4

公开(公告)日：2017-06-07

申请号：EP14865153

申请日：2014-09-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GAYMAN SCOTT W ,  SPANGLER BRANDON W

IPC: F01D5/18 ,  F02C7/18

CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2250/185

Abstract: A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end. A platform cooling passageway is fluidly connected to the end and extends transversely into the platform. A cooling hole fluidly connects the platform cooling passageway to an exterior surface.

Abstract translation: 燃气涡轮发动机翼型包括平台和间隔开的壁，所述壁提供从平台径向地延伸到与平台相对的端部的外部翼型表面。 蜿蜒的冷却通道布置在壁之间并且具有从平台朝向端部延伸的第一通道和流体地连接到第一通道并且从端部朝向平台延伸到端部的第二通道。 平台冷却通道流体连接到端部并横向延伸到平台中。 冷却孔将平台冷却通道流体连接到外表面。

公开(公告)号：EP3044418A4

公开(公告)日：2017-05-17

申请号：EP14842280

申请日：2014-08-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  OTERO EDWIN

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58

CPC classification number: F01D5/187 ,  B22C9/04 ,  B22C9/046 ,  B22C9/103 ,  B28B1/30 ,  B28B7/34 ,  F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2250/232 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

Abstract translation: 燃气涡轮发动机部件包括具有间隔开的第一和第二外壁的结构，所述第一和第二外壁沿第一方向延伸至端壁。 第一和第二外壁在端壁处连接以提供冷却腔。 叉形挡板布置在冷却腔中并且包括分别与第一和第二外壁相邻的第一和第二内壁。 第一和第二内壁在第一方向上延伸至三角胶并与其连接以提供第一空腔。 叉形挡板将第一腔体与设置在顶端和端壁之间的第二腔体分隔开。