公开(公告)号：CA2495740A1

公开(公告)日：2005-08-03

申请号：CA2495740

申请日：2005-02-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TELLER BRET ,  CUNHA FRANK ,  SANTELER KEITH

IPC: F01D5/14 ,  F01D5/18 ,  F02C7/18 ,  F01D5/30

Abstract: A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro- circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro- circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal connective efficiency, high film coverage, and high cooling effectiveness.

公开(公告)号：SG122911A1

公开(公告)日：2006-06-29

申请号：SG200507274

申请日：2005-11-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  PIETRASZKIEWICZ EDWARD F ,  KONTROVITZ DAVID M ,  LEVINE JEFFREY R ,  CHON YOUNG ,  MONGILLO DOMINIC ,  TELLER BRET

Abstract: An airfoil (59), and in a disclosed embodiment a rotor blade, has film cooling holes (48) formed at a leading edge (41). A supplemental film cooling channel (60) is positioned near the leading edge (41), but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel (60) directs film cooling air onto a suction wall (38). The supplemental film cooling channel air is generally directed to a location on the suction wall (38) that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.

公开(公告)号：DE602005027139D1

公开(公告)日：2011-05-12

申请号：DE602005027139

申请日：2005-02-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SANTELER KEITH ,  TELLER BRET ,  CUNHA FRANK

IPC: F01D5/14 ,  F01D5/18 ,  F02C7/18

公开(公告)号：SG122040A1

公开(公告)日：2006-05-26

申请号：SG200508439

申请日：2005-10-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  TELLER BRET ,  CHON YOUNG ,  MONGILLO DOMINIC ,  PIETRASZKIEWICZ EDWARD F

Abstract: An airfoil (34), and in a disclosed embodiment a rotor blade, has a serpentine cooling path. To best account for the Coriolis effect, the paths of the serpentine cooling channel have trapezoidal cross-sections. An area of the rotor blade between a smaller side (43) of the trapezoidal-shaped paths, and a facing wall (46) of the rotor blade has high thermal and mechanical stresses, and is a challenge to adequately cool. A microcircuit (50), which is a very thin cooling circuit having crossing pedestals (112), is embedded into the blade in this area. The microcircuit provides additional cooling, and addresses the challenges with regard to cooling these areas.