Fatigue resistant blade outer air seal

Patent metadata

Field	Value
Publication number	US-11619136-B2
Application number	US-201916434630-A
Country	US
Kind code	B2
Filing date	Jun 7, 2019
Priority date	Jun 7, 2019
Publication date	Apr 4, 2023
Grant date	Apr 4, 2023

Abstract

A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss. The blade outer air seal segment further including a stress-relief recess. The stress-relief boss being located within the stress relief recess.

First claim

What is claimed is:

1. A blade outer air seal segment, comprising:
a radially outward surface;
a radially inward surface oriented away from the radially outward surface, a radially outward wall interposed between the radially outward surface and the radially inward surface;
a cooling channel located between the radially outward surface and the radially inward surface;
a stress-relief boss extending into the cooling channel;
an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss;
a stress-relief recess, the stress-relief boss being located within the stress-relief recess;
wherein the cooling channel is defined, at least partially, by a radially outward channel surface and a radially inward channel surface;
wherein the stress-relief boss extends away from the radially outward channel surface to a surface of the stress-relief boss;
wherein a thickness of the radially outward wall between the radially outward surface and the surface of the stress-relief boss is greater than a thickness of the radially outward wall between the radially outward surface and the radially outward channel surface, and wherein a radial height of the cooling channel at a base of the stress-relief recess is greater than any other radial height of the cooling channel.

2. The blade outer air seal segment of claim 1 , further comprising:
a raised portion of the radially outward surface, wherein the radially outward channel surface is located radially outward of the radially inward channel surface, and wherein the inlet orifice extends from the raised portion of the radially outward surface to the surface of the stress-relief boss.

3. The blade outer air seal segment of claim 1 ,
wherein the surface of the stress-relief boss is parallel to at least one of the radially inward channel surface and the radially outward channel surface.

4. The blade outer air seal segment of claim 1 , wherein a radial height of the cooling channel between the radially outward channel surface and the radially inward channel surface is greater than a radial height of the cooling channel between the surface of the stress-relief boss and the radially inward channel surface.

5. The blade outer air seal segment claim 1 , wherein the stress-relief boss is concentric to the inlet orifice.

6. The blade outer air seal segment claim 1 , wherein the stress-relief boss is concentric to the stress-relief recess.

7. The blade outer air seal segment of claim 1 , wherein the stress-relief recess extends into the radially outward channel surface to the base of the stress-relief recess.

8. The blade outer air seal segment of claim 7 , wherein a radial height of the cooling channel between the radially outward channel surface and the radially inward channel surface is less than the radial height of the cooling channel between the base of the stress-relief recess and the radially inward channel surface.

9. A turbine section of a gas turbine engine, the turbine section comprising:
a blade configured to rotate about an axis; and
a blade outer air seal segment radially outward of the blade, the blade outer air seal segment comprising:
a radially outward surface;
a radially inward surface oriented away from the radially outward surface, a radially outward wall interposed between the radially outward surface and the radially inward surface;
a cooling channel located between the radially outward surface and the radially inward surface;
a stress-relief boss extending into the cooling channel;
an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss;
a stress-relief recess, the stress-relief boss being located within the stress-relief recess;
wherein the cooling channel is defined, at least partially, by a radially outward channel surface and a radially inward channel surface;
wherein the stress-relief boss extends away from the radially outward channel surface to a surface of the stress-relief boss; and
wherein a thickness of the radially outward wall between the radially outward surface and the surface of the stress-relief boss is greater than a thickness of the radially outward wall between the radially outward surface and the radially outward channel surface, and wherein a radial height of the cooling channel directly at a base of the stress-relief recess is greater than any other radial height of the cooling channel.

10. The turbine section of claim 9 , further comprising:
a raised portion of the radially outward surface, wherein the radially outward channel surface is located radially outward of the radially inward channel surface, and wherein the inlet orifice extends from the raised portion of the radially outward surface to the surface of the stress-relief boss.

11. The turbine section of claim 9 , wherein the surface of the stress-relief boss is parallel to at least one of the radially inward channel surface and the radially outward channel surface.

12. The turbine section of claim 9 , wherein a radial height of the cooling channel between the radially outward channel surface and the radially inward channel surface is greater than a radial height of the cooling channel between the surface of the stress-relief boss and the radially inward channel surface.

13. The turbine section of claim 9 , wherein the stress-relief boss is concentric to the inlet orifice.

14. The turbine section of claim 9 , wherein the stress-relief boss is concentric to the stress-relief recess.

15. The turbine section of claim 9 , wherein the stress-relief recess extends into the radially outward channel surface to the base of the stress-relief recess.

16. The turbine section of claim 15 , wherein a radial height of the cooling channel between the radially outward channel surface and the radially inward channel surface is less than the radial height of the cooling channel between the base of the stress-relief recess and the radially inward channel surface.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Mclaughlin Brian C
• Lutjen Paul M
• Hayford Richard K
• Swift Anthony B

Classifications

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D5/187

  Convection cooling · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title