Turbomachine component with coating-capturing feature for thermal insulation
The disclosure relates to turbomachine components which include one or more coating-capturing features for thermal insulation. A turbomachine component may include: a body having an exterior surface positioned within a hot gas path (HGP) section of a turbomachine; and a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature comprises: a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature, a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body, and an indentation positioned between the first and second members.
1. A turbomachine component for a turbomachine comprising:
a body having an exterior surface positioned within a hot gas path (HGP) section of the turbomachine; and
a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature includes:
a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature,
a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body,
an indentation positioned between the first and second members, wherein at least a portion of the indentation has a width narrower than portions of the first and second members; and
a cooling passage formed within the coating-capturing feature, wherein the cooling passage includes an inlet fluidly coupled to an interior of the body and an outlet fluidly coupled through the at least one outer sidewall of the first member or the at least one outer sidewall of the second member.
2. The turbomachine component of claim 1 , wherein the coating-capturing feature and the body each include a laser-sintered metal.
3. The turbomachine component of claim 1 , further comprising a surface coating positioned on the body and the coating-capturing feature, wherein the surface coating includes:
a base coating layer conformally coated on the exterior surface of the body, the at least one sidewall of the first member of the coating-capturing feature, and the at least one sidewall of the second member of the coating-capturing feature, wherein the base coating layer is positioned at least partially within the indentation of the coating-capturing feature,
a first thermal barrier coating (TBC) layer positioned on the base coating layer, and
a second TBC layer positioned on the first TBC layer.
4. The turbomachine component of claim 3 , wherein each of the base coating layer, the first TBC layer, and the second TBC layer have a different material composition.
5. The turbomachine component of claim 1 , wherein the coating-capturing feature extends outward from the body at a non-perpendicular angle relative to the exterior surface of the body.
6. The turbomachine component of claim 1 , wherein the body comprises part of a nozzle or a rotating blade positioned within the HGP section of the turbomachine.
7. The turbomachine component of claim 1 , wherein the first member of the coating-capturing feature is frusto-pyramidal or frusto-conical, and wherein the second member of the coating-capturing feature is spheroidal.
8. The turbomachine component of claim 1 , further comprising an adhesive bond interposed between the first member of the coating-capturing feature and the exterior surface of the body.
9. An apparatus comprising:
a turbomachine component having an exterior surface for positioning within a hot gas path (HGP) section of a turbomachine;
a coating-capturing feature mounted on the exterior surface of the turbomachine component and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature comprises:
a first member positioned on the exterior surface of the turbomachine component, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature,
a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the turbomachine component, and
an indentation positioned between the first and second members; and a surface coating comprising:
a base coating layer conformally coated on the exterior surface of the turbomachine component, the at least one sidewall of the first member of the coating-capturing feature, and the at least one sidewall of the second member of the coating-capturing feature, wherein the base coating layer is positioned at least partially within the indentation of the coating-capturing feature,
at least one thermal barrier coating (TBC) layer positioned on the base coating layer, wherein at least a portion of the indentation has a width narrower than portions of the first and second members, and
a cooling passage formed within the coating-capturing feature, wherein the cooling passage includes an inlet fluidly coupled to an interior of the turbomachine component and an outlet fluidly coupled through the at least one outer sidewall of the first member or the at least one outer sidewall of the second member.
10. The apparatus of claim 9 , wherein each of the base coating layer and the at least one TBC layer have a different material composition.
11. The apparatus of claim 9 , wherein the coating-capturing feature extends outward from the turbomachine component at a non-perpendicular angle relative to the exterior surface of the turbomachine component.
12. The apparatus of claim 9 , wherein the first member of the coating-capturing feature is frusto-pyramidal or frusto-conical, and wherein the second member of the coating-capturing feature is spheroidal.
13. The apparatus of claim 9 , wherein the turbomachine component and the coating-capturing feature each include a laser-sintered metal.
14. A turbomachine component for a turbomachine, comprising:
a body having an exterior surface positioned within a hot gas path (HGP) section of the turbomachine; and
a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature includes:
a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature,
a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body, and
an indentation positioned between the first and second members,
wherein the coating-capturing feature includes a hollow interior extending from within the first member of the coating-capturing feature to an outermost end of the second member of the coating-capturing feature.
15. The turbomachine component of claim 14 , wherein the coating-capturing feature includes an inlet fluidly coupled to an interior of the body and an outlet fluidly coupled through the at least one outer sidewall of the first member or the at least one outer sidewall of the second member.
16. The turbomachine component of claim 14 , further comprising a surface coating positioned on the body and the coating-capturing feature, wherein the surface coating includes:
a base coating layer conformally coated on the exterior surface of the body, the at least one sidewall of the first member of the coating-capturing feature, and the at least one sidewall of the second member of the coating-capturing feature, wherein the base coating layer is positioned at least partially within the indentation of the coating-capturing feature,
a first thermal barrier coating (TBC) layer positioned on the base coating layer, and
a second TBC layer positioned on the first TBC layer.
17. The turbomachine component of claim 16 , wherein each of the base coating layer, the first TBC layer, and the second TBC layer have a different material composition.
18. The turbomachine component of claim 14 , wherein the coating-capturing feature extends outward from the body at a non-perpendicular angle relative to the exterior surface of the body.
19. The turbomachine component of claim 14 , wherein the first member of the coating-capturing feature is frusto-pyramidal or frusto-conical, and wherein the second member of the coating-capturing feature is spheroidal.