公开(公告)号：WO2015080783A2

公开(公告)日：2015-06-04

申请号：PCT/US2014055332

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件包括平台和间隔开的壁，其提供从平台径向延伸到与平台相对的端部的外部翼面表面。 蛇形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连接到第一通道并从端部朝向平台延伸到端部的第二通道。 平台冷却通道流体地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畅地连接到外表面。

公开(公告)号：DE602005000449D1

公开(公告)日：2007-03-08

申请号：DE602005000449

申请日：2005-03-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  SANTELER KEITH ,  GAYMAN SCOTT W ,  COUCH ERIC

IPC: F01D5/00 ,  F01D5/18 ,  F01D5/08 ,  F02C7/16 ,  F02C7/18

Abstract: A turbine airfoil includes a plurality of cooling circuits (22) embedded within the pressure and suction sidewalls (28,30) and a first and a second flow passage (32f,32g). The first flow passage (32f) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the pressure sidewall (28) and the second flow passage (32g) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the suction sidewall (30).

公开(公告)号：SG127789A1

公开(公告)日：2006-12-29

申请号：SG200601656

申请日：2006-03-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  COUCH ERIC ,  SANTELER KEITH A ,  GAYMAN SCOTT W ,  HUDSON ERIC A ,  JOE CHRISTOPHER ,  LETIZIA ERIC

Abstract: An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.

公开(公告)号：PL1577498T3

公开(公告)日：2007-06-29

申请号：PL05251603

申请日：2005-03-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  SANTELER KEITH ,  GAYMAN SCOTT W ,  COUCH ERIC

IPC: F01D5/00 ,  F01D5/18 ,  F01D5/08 ,  F02C7/16 ,  F02C7/18

公开(公告)号：DE602005000449T2

公开(公告)日：2007-08-23

申请号：DE602005000449

申请日：2005-03-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  SANTELER KEITH ,  GAYMAN SCOTT W ,  COUCH ERIC

IPC: F01D5/00 ,  F01D5/18 ,  F01D5/08 ,  F02C7/16 ,  F02C7/18

Abstract: A turbine airfoil includes a plurality of cooling circuits (22) embedded within the pressure and suction sidewalls (28,30) and a first and a second flow passage (32f,32g). The first flow passage (32f) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the pressure sidewall (28) and the second flow passage (32g) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the suction sidewall (30).

公开(公告)号：CA2497755A1

公开(公告)日：2005-09-16

申请号：CA2497755

申请日：2005-02-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SANTELER KEITH ,  CUNHA J FRANK ,  COUCH ERIC ,  GAYMAN SCOTT W

IPC: F01D5/00 ,  F01D5/08 ,  F01D5/18 ,  F02C7/16 ,  F02C7/18 ,  F01D9/02 ,  F01D25/12

Abstract: A turbine airfoil includes a plurality of cooling circuits embedded within t he pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.

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。