公开(公告)号：AU2007200773A1

公开(公告)日：2008-09-04

申请号：AU2007200773

申请日：2007-02-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHIN KAR D ,  SHARMA OM P ,  PIETRASZKIEWICS EDWARD F

IPC: F01D5/18 ,  F01D5/08

Abstract: A turbine blade (14) is cooled by cooling air that flows through a radial cooling channel (40). The turbine blade (14) includes a root (20) and an airfoil (22). The flow of cooling air into the cooling channel (40) is limited by a pre-meter orifice (52) to provide a reduced pressure within the cooling channel (40). The pressure drop results from the cross-sectional area (A O ) of the pre-meter orifice (52) being less than the cross-sectional area (A C ) of the adjacent cooling channel (40). After flowing through the cooling channel (40), the cooling air exits the cooling channel (40) through a film hole (38) to form a film layer over the airfoil (22) to cool and insulate the turbine blade (14).