公开(公告)号：US20160312654A1

公开(公告)日：2016-10-27

申请号：US15105443

申请日：2014-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Pritchaiah Vijay Chakka ,  Andrew S. Aggarwala ,  Thomas J. Praisner ,  Brandon W. Spangler

IPC: F01D25/12 ,  F01D9/02 ,  F02C3/04 ,  F01D5/12

CPC classification number: F01D25/12 ,  F01D5/12 ,  F01D5/145 ,  F01D9/02 ,  F02C3/04 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.

Abstract translation: 翼型组件在至少一个平台的后边缘中具有至少一个冷却孔，用于冷却轴向下游的翼型根部和/或尖端区域中的至少一个。 翼型组件可以是与以低模式因数运行的燃烧器相连的高压涡轮机第一级叶片。