公开(公告)号：WO2015073092A3

公开(公告)日：2015-08-06

申请号：PCT/US2014052850

申请日：2014-08-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THISTLE CHARLES ,  THORNTON LANE

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.

Abstract translation: 燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。 冷却通道提供具有在负载方向上延伸的大致直的部分和横向于负载方向的弯曲的曲折通道。 细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。 细长的湍流器基本上在大致直的部分内。

公开(公告)号：WO2015160404A3

公开(公告)日：2016-03-10

申请号：PCT/US2015012119

申请日：2015-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THISTLE CHARLES ,  THORNTON LANE

IPC: F02C7/16 ,  F01D5/18 ,  F01D25/12

CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F01D11/24 ,  F02C3/10 ,  F02C7/12 ,  F02K3/06 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/121 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676

Abstract: A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.

Abstract translation: 燃气涡轮发动机部件包括在两端之间延伸并且具有至少两个冷却通道的主体。 身体有第一个墙壁和第二个墙壁。 至少两个冷却通道包括比沿着流动路径的上游位置处的第二通道更靠近第一壁的第一通道。 第二通道具有比第一通道的上游部分更靠近第二壁的上游位置。 所述第一通道和所述第二通道沿所述流动路径的长度交叉，使得所述第二通道的下游部分比所述第一通道的下游部分更靠近所述第一壁，并且所述第一通道的下游部分比所述第一通道的下游部分更靠近所述第二壁 是第二通道的下游部分。

公开(公告)号：EP3042041A4

公开(公告)日：2016-09-28

申请号：EP14862682

申请日：2014-08-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THISTLE CHARLES ,  THORNTON LANE

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion.

Abstract translation: 燃气涡轮发动机部件包括在负载方向上延伸并提供冷却通道的间隔开的壁。 冷却通道提供具有在负载方向上延伸的大致直线部分和横向于负载方向的弯曲部的曲折通道。 细长的湍流器从至少一个壁突出并基本上在负载方向上延伸。 细长的湍流器基本上在大致直的部分内。

公开(公告)号：EP3105436A4

公开(公告)日：2017-03-08

申请号：EP15779486

申请日：2015-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THISTLE CHARLES ,  THORNTON LANE

IPC: F01D5/18 ,  F01D11/24 ,  F01D25/12

CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F01D11/24 ,  F02C3/10 ,  F02C7/12 ,  F02K3/06 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/121 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676

公开(公告)号：EP3080416A4

公开(公告)日：2017-08-30

申请号：EP14869625

申请日：2014-12-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THISTLE CHARLES ,  THORNTON LANE

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/081 ,  F01D5/186 ,  F01D5/3007 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/202 ,  F05D2260/22141 ,  F23R3/002

Abstract: A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A pedestal is arranged in the cooling passage and interconnects the walls in a thickness direction that is transverse to the first direction. The pedestal is asymmetrical in the thickness direction.

Abstract translation: 燃气涡轮发动机部件包括间隔开的壁，其提供沿第一方向延伸的冷却通道。 基座布置在冷却通道中并且在与第一方向横切的厚度方向上将壁互连。 底座在厚度方向上是不对称的。