公开(公告)号：US20160123156A1

公开(公告)日：2016-05-05

申请号：US14872511

申请日：2015-10-01

Applicant: ROLLS-ROYCE PLC

Inventor： Paul A. HUCKER ,  Stephen C. HARDING ,  Alan P. GEARY

IPC: F01D5/18 ,  F23R3/00

CPC classification number: F01D5/186 ,  F01D5/188 ,  F01D9/065 ,  F05B2260/202 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043

Abstract: A cooled gas turbine engine component comprises a wall having first and second surfaces. The second surface has a plurality of recesses and each recess has a planar upstream end surface arranged so that it hangs over the upstream end of the recess. Each recess has a depth equal to the required depth plus the thickness of the thermal barrier coating to be deposited. The wall has a plurality of angled effusion cooling apertures extending from the first surface towards the second surface. Each effusion cooling aperture has an inlet in the first surface and an outlet in the end surface of a corresponding one of the recesses in the second surface. Each recess has smoothly curved transitions from the end surface and side surfaces to the second surface. Blocking of the effusion cooling apertures by thermal barrier coating is reduced.

Abstract translation: 冷却的燃气涡轮发动机部件包括具有第一和第二表面的壁。 第二表面具有多个凹部，并且每个凹部具有布置成使其悬挂在凹部的上游端上的平坦的上游端面。 每个凹槽的深度等于所要求的深度加上待沉积的热障涂层的厚度。 壁具有从第一表面朝向第二表面延伸的多个倾斜的积水冷却孔。 每个排出冷却孔在第一表面中具有入口，在第二表面中的相应的一个凹部的端面中具有出口。 每个凹部具有从端表面和侧表面到第二表面的平滑弯曲过渡。 通过热障涂层阻挡积液冷却孔。