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.