公开(公告)号：US10526906B2

公开(公告)日：2020-01-07

申请号：US15081079

申请日：2016-03-25

Applicant: SNECMA

Inventor： David Thien-Roger Nguyen ,  Franck Boisnault ,  Maurice Guy Judet ,  Laetitia Person

IPC: F01D11/02 ,  F01D5/18 ,  F01D11/04

Abstract: A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.