公开(公告)号：US09506348B2

公开(公告)日：2016-11-29

申请号：US14355983

申请日：2012-11-02

Applicant: GE AVIO S.r.L.

Inventor： Francesco Bertini

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/145 ,  F05D2230/00 ,  Y02T50/673 ,  Y10T29/49336

Abstract: According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer.

Abstract translation: 根据该方法，从基准机翼开始制造涡轮机翼，在两个区域中局部减小后缘处的金属出口角，这两个区域在使用中基本对应于边界层中次流的峰值位置 。