公开(公告)号：US20170101932A1

公开(公告)日：2017-04-13

申请号：US15314490

申请日：2015-05-27

Applicant: General Electric Company

Inventor： Curtis Walton STOVER ,  Jonathan Michael RAUSCH ,  Satoshi ATSUCHI ,  Gulcharan Singh BRAINCH ,  Robert David BRIGGS ,  Ronald Scott BUNKER ,  Ambarish Jayant KULKARNI ,  Michael Alan MEADE ,  Byron Andrew PRITCHARD ,  Robert PROCTOR

IPC: F02C7/18 ,  F01D11/08 ,  F01D25/12 ,  F01D9/04

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.