公开(公告)号：US20150152745A1

公开(公告)日：2015-06-04

申请号：US14407918

申请日：2013-06-14

Applicant: GE AVIO S.R.L.

Inventor： Daniele Countandin ,  Stefano Zecchi

IPC: F01D25/14

CPC classification number: F01D25/12 ,  F01D11/24 ,  F01D25/145 ,  F02C7/18 ,  F05D2220/32 ,  F05D2250/712 ,  F05D2260/201 ,  F05D2260/231 ,  Y02T50/672 ,  Y02T50/676

Abstract: In a gas turbine for aeronautic engines, a stator body delimited by an outer lateral surface is cooled by an air cooling device having a plurality of circumferential tubes for distributing air on the outer lateral surface; each circumferential tube having a plurality of outlets for guiding respective cooling airflows towards the outer lateral surface and into a respective circumferential channel obtained between two groups of circumferential channels adjacent to each other and lapped by the flow of air leaving the circumferential channel.

Abstract translation: 在用于航空发动机的燃气轮机中，由外侧表面限定的定子体由具有多个用于在外侧表面上分配空气的多个圆周管的空气冷却装置来冷却; 每个圆周管具有多个出口，用于将相应的冷却气流朝向外侧表面引导并且进入相邻的两组圆周通道之间获得的相应的圆周通道，并通过离开圆周通道的空气流进行研磨。