Cooled component

Patent metadata

Field	Value
Publication number	US-9957811-B2
Application number	US-201514872511-A
Country	US
Kind code	B2
Filing date	Oct 1, 2015
Priority date	Oct 30, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

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.

First claim

The invention claimed is:

1. A cooled component comprising a wall having a first surface and a second surface, the second surface having a plurality of recesses, each recess of the plurality of recesses having an upstream end and a downstream end, each recess of the plurality of recesses having a planar upstream end surface arranged at a first angle of more than 100° to the second surface such that the planar upstream end surface hangs over the upstream end of the respective recess, each recess of the plurality of recesses having a first smoothly curved transition from the planar upstream end surface to the second surface, each recess of the plurality of recesses reducing in depth from the upstream end of the recess to the downstream end of the recess, each recess of the plurality of recesses having side surfaces, wherein each side surface of each respective recess is arranged at a second angle of less than 80° to the second surface and each recess of the plurality of recesses having second smoothly curved transitions from the side surfaces to the second surface, the wall having a plurality of effusion cooling apertures extending there-through from the first surface towards the second surface, each effusion cooling aperture of the plurality of effusion cooling apertures being arranged at a third angle to the first surface, each effusion cooling aperture of the plurality of effusion cooling apertures having an inlet in the first surface and an outlet in a corresponding recess of the plurality of recesses in the second surface, each effusion cooling aperture of the plurality of effusion cooling apertures extending from the first surface to the planar upstream end surface of the corresponding recess of the plurality of recesses in the second surface.

2. The cooled component as claimed in claim 1 , wherein the side surfaces of each recess of the plurality of recesses converge from the upstream end of the recess to the downstream end of the recess.

3. The cooled component as claimed in claim 2 , wherein each recess of the plurality of recesses has a shaped opening in the second surface selected from the group consisting of: a triangular shaped opening in the second surface and a part elliptically shaped opening in the second surface.

4. The cooled component as claimed in claim 1 , wherein the side surfaces of each recess of the plurality of recesses diverge from one another from the upstream end of the recess to the downstream end of the recess.

5. The cooled component as claimed in claim 4 , wherein each recess of the plurality of recesses has an isosceles trapezium shaped opening in the second surface.

6. The cooled component as claimed in claim 1 , wherein the side surfaces of each recess of the plurality of recesses are parallel to one another from the upstream end of the recess to the downstream end of the recess.

7. The cooled component as claimed in claim 6 , wherein each recess of the plurality of recesses has a shaped opening in the second surface selected from the group consisting of: a rectangular shaped opening in the second surface, a square shaped opening in the second surface and a rhombus shaped opening in the second surface.

8. The cooled component as claimed in claim 1 , wherein each effusion cooling aperture of the plurality of effusion cooling apertures has a metering portion between the inlet and the outlet.

9. The cooled component as claimed in claim 1 , wherein each effusion cooling aperture of the plurality of effusion cooling apertures has a metering portion and a diffusing portion arranged in flow series between the inlet and the outlet.

10. The cooled component as claimed in claim 1 , wherein each effusion cooling aperture of the plurality of effusion cooling apertures is arranged parallel to a bottom of the corresponding recess of the plurality of recesses.

11. The cooled component as claimed in claim 1 , wherein the first angle is 105° to the second surface.

12. The cooled component as claimed in claim 1 , wherein the second angle is 75° to the second surface.

13. The cooled component as claimed in claim 1 , wherein the inlet of each effusion cooling aperture of the plurality of effusion cooling apertures in the first surface is an elliptically shaped inlet.

14. The cooled component as claimed in claim 1 , wherein each effusion cooling aperture has a circular cross-section metering portion.

15. The cooled component as claimed in claim 9 , wherein each effusion cooling aperture of the plurality of effusion cooling apertures diverges in the diffusing portion.

16. The cooled component as claimed in claim 8 , wherein the metering portion is arranged at an angle of between 10° and 30° to the first surface.

17. The cooled component as claimed in claim 1 , wherein the cooled component has a thermal barrier coating on the second surface, each recess of the plurality of recesses having a depth equal to a finished depth plus a thickness of the thermal barrier coating to be deposited.

18. The cooled component as claimed in claim 1 , wherein the cooled component comprises a second wall, the second wall having a third surface and a fourth surface, the fourth surface of the second wall being spaced from the first surface of the wall and the second wall having a plurality of impingement cooling apertures extending there-through from the third surface to the fourth surface.

19. The cooled component as claimed in claim 1 , wherein the cooled component is selected from the group consisting of: a turbine blade, a turbine vane, a combustion chamber wall, a combustion chamber tile, a combustion chamber heat shield, a combustion chamber wall segment, and a turbine shroud.

20. The cooled component as claimed in claim 19 , wherein the cooled component is an annular combustion chamber wall and the annular combustion chamber wall has each recess of the plurality of recesses arranged such that each planar upstream end surface of the respective recess, which extends laterally, extends circumferentially around the annular combustion chamber wall and the side surfaces, which extend longitudinally, extend axially with respect to the annular combustion chamber wall.

21. The cooled component as claimed in claim 19 , wherein the cooled component is the combustion chamber tile for an annular combustion chamber wall and the combustion chamber tile has each recess of the plurality of recesses arranged such that each planar upstream end surface of the respective recess, which extends laterally, extends circumferentially around the combustion chamber tile and the side surfaces, which extend longitudinally, extend axially with respect to the combustion chamber tile.

22. The cooled component as claimed in claim 19 , wherein the cooled component is the combustion chamber wall segment for an annular combustion chamber wall and the combustion chamber wall segment comprises an outer wall and an inner wall, wherein the outer wall is spaced from the inner wall, the outer wall has a plurality of impingement cooling apertures and the inner wall has the plurality of effusion cooling apertures, the inner wall has each recess of the plurality of recesses arranged such that each planar upstream end surface of the respective recess, which extends laterally, extends circumferentially of the combustion chamber wall segment and the side surfaces, which extend longitudinally, extend axially with respect to the combustion chamber wall segment.

23. The cooled component as claimed in claim 1 , wherein the cooled compo

Assignees

• Rolls Royce Plc

Inventors

• Hucker Paul A
• Harding Stephen C
• Geary Alan P

Classifications

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F01D5/188

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title