公开(公告)号：CA2475889A1

公开(公告)日：2005-02-08

申请号：CA2475889

申请日：2004-07-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA J FRANK

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

Abstract: A turbine blade is provided comprising an internal cavity into which cooling air is flowable, an external wall and a first, second and third cooling circuits embedded with the wall. The cooling circuits include inlets that connect each respective cooli ng circuit with cavity to provide a cooling air flow path into the respective cooling circui t. The cooling circuits also include an exit aperture that provides a cooling air flow path out of the respective cooling circuits. The cooling circuits are configured to increase the temperature of the cooling air as it travels from the inlet to the exit aperture. In the exemplary embodiment, the inlets are aligned with the direction of counter-rotating flow circulations experienced by the inner surface of the wall caused by Coriolis flow effects on the cooling air flowing inside the cavity.

公开(公告)号：CA2456628A1

公开(公告)日：2004-08-05

申请号：CA2456628

申请日：2004-02-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA J FRANK ,  DUBLE P BRYAN

IPC: F01D5/08 ,  F01D5/18 ,  F01D5/30 ,  F02C7/18 ,  F01D25/12

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip between a suction sidewall and a pressure sidewall of the airfoil. The microcircuit includes at least on inlet disposed proximate to the tip and one of the sidewalls for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet disposed proximat e to the tip through which the cooling air ejects into a region outside the airfoil.

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：CA2475885A1

公开(公告)日：2005-02-08

申请号：CA2475885

申请日：2004-07-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA J FRANK ,  SANTELER KEITH A

IPC: F01D5/18 ,  F02C7/18

Abstract: A cooling circuit disposed within a first wall portion and a second wall portion of a wall for use in a gas turbine engine is provided. The cooling circuit includ es a plurality of inlet apertures disposed in the first wall portion to provide a flow path of cooling air into the cooling circuit, a first exit slot disposed in the second wall portion to provide a cooling air flow path out of the cooling circuit, a plurality of pedestals arranged in rows extending within the between the first wall portion and the second wall portion and a first elongated pedestal disposed radially and extending between the first and second wall portions. The first elongated pedestal is positioned between the pedestals and the first exit slot.

公开(公告)号：CA2462986A1

公开(公告)日：2004-10-07

申请号：CA2462986

申请日：2004-04-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PALUMBO MICHAEL A ,  CUNHA J FRANK

IPC: F01D5/18 ,  F01D25/12

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the plenum are positioned a plurality of turbulence promoters to provide enhanced heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets to receive cooling air from an internal cavity of the airfoil as well as a plurality of outlets located within a trench on the exterior surface of the leading edge through which the cooling air exits to film cool the leading edge.