公开(公告)号：US20160017717A1

公开(公告)日：2016-01-21

申请号：US14837014

申请日：2015-08-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. PROPHETER-HINCKLEY ,  Rafael A. PEREZ ,  Edward F. PIETRASZKIEWICZ

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D9/041 ,  F05D2240/12 ,  F05D2250/185 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的翼型件尤其包括设置在翼型体内部的翼型体和冷却回路，并且包括前缘腔，第一部分从径向内壁 到所述翼型件本体的径向外壁，以及从所述翼型件主体的前缘内壁延伸到后缘内壁的第二部分。 冷却回路构造成在冷却回路的第二腔体离开前缘空腔之前将冷却气流通过第一部分和第二部分。