公开(公告)号：CA2523630A1

公开(公告)日：2006-05-09

申请号：CA2523630

申请日：2005-10-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOTNICK CHRISTINA ,  PIETRASZKIEWICZ EDWARD F ,  COONS TODD

IPC: B64C3/36 ,  F28F3/12 ,  F28F13/12

Abstract: A turbine blade airfoil assembly includes a cooling air passage. The cooli ng air passage includes a plurality of impingement openings that are isolated from at least one adjacent impingement opening. The cooling air passage is formed an d cast within a turbine blade assembly through the use of a single core. The single core forms the features required to fabricate the various separate and isolated impingement openings. The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.

公开(公告)号：SG122883A1

公开(公告)日：2006-06-29

申请号：SG200506801

申请日：2005-10-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PIETRASZKIEWICZ EDWARD F ,  BOTNICK CHRISTINA ,  COONS TODD

Abstract: A turbine blade airfoil assembly (12) includes a cooling air passage (30). The cooling air passage (30) includes a plurality of impingement openings (32) that are isolated from at least one adjacent impingement opening (32). The cooling air passage (30) is formed and cast within a turbine blade assembly through the use of a single core (44). The single core (44) forms the features required to fabricate the various separate and isolated impingement openings (32). The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.