公开(公告)号：US20160281525A1

公开(公告)日：2016-09-29

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

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.

Abstract translation: 一种用于飞机涡轮机的涡轮叶片，包括根部，翼型件和插入在翼型件和根部之间并限定气体循环流动路径的平台，该平台具有两个轴向端，每个端部形成天使翼，其中至少一个具有内部空腔 将从叶片的根部提供空气。 两个天使翼中至少有一个钻有至少一个排放孔，用于从内腔通过渗流，这将限制/防止在流路外的气体再循环。