Fatigue resistant blade outer air seal

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.