Hot gas path component
Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
1. A turbomachine component comprising:
a first portion including at least one of a stainless steel or an alloy steel; and
a second portion joined with the first portion, the second portion including a nickel alloy and including an arced pathway extending therethrough having an outlet, the second portion having a thermal expansion coefficient differing by 5 percent to 25 percent from a thermal expansion coefficient of the first portion, the second portion having a leakage surface configured to be circumferentially facing and located in an axial-radial plane of a turbomachine, the leakage surface including the outlet,
wherein the arced pathway is configured to direct a portion of a coolant to a leakage area of the turbomachine component by way of the outlet, wherein the arced pathway loops back over itself in a radial direction in a plane perpendicular to the axial-radial plane.
2. The turbomachine component of claim 1 , further comprising a weld joint or a braze joint bonding the second portion to the first portion.
3. The turbomachine component of claim 1 , wherein the first portion and the second portion collectively form a gas turbine shroud.
4. The turbomachine component of claim 3 , further comprising a turbomachine airfoil connected with the gas turbine shroud.
5. The turbomachine component of claim 4 , wherein the turbomachine airfoil and the gas turbine shroud form a bucket or a nozzle.
6. The turbomachine component of claim 1 , wherein the arced pathway has a serpentine shape and is fluidly coupled with a cooling pathway extending through the second portion.
7. A turbomachine component comprising:
a first portion including at least one of a stainless steel or an alloy steel; and
a second portion joined with the first portion, the second portion including a nickel alloy and including an arced pathway extending therethrough having an outlet, the second portion having a thermal expansion coefficient differing by less than 25 percent from a thermal expansion coefficient of the first portion, the second portion having a leakage surface configured to be circumferentially facing and located in an axial-radial plane of a turbomachine, the leakage surface including the outlet
wherein the arced pathway is configured to direct a portion of a coolant to a leakage area of the turbomachine component by way of the outlet, wherein the arced pathway includes a series of intersecting plenums for allowing flow of the coolant to loop back over in a radial direction in a plane perpendicular to the axial-radial plane,
wherein the first portion and the second portion collectively form a turbomachine shroud.
8. The turbomachine component of claim 7 , further comprising a turbomachine airfoil coupled with the turbomachine shroud.
9. A set of turbomachine buckets, comprising:
a plurality of adjacent turbomachine buckets each having:
a shroud including:
a first portion including at least one of a stainless steel or an alloy steel; and
a second portion joined with the first portion, the second portion including a nickel alloy and including an arced pathway extending therethrough having an outlet, the second portion having a thermal expansion coefficient differing by less than 25 percent from a thermal expansion coefficient of the first portion, the second portion having a leakage surface configured to be circumferentially facing and located in an axial-radial plane of a turbomachine, the leakage surface including the outlet; and
a turbomachine airfoil coupled with the shroud,
wherein the arced pathway is configured to direct a portion of a coolant to a leakage area of the turbomachine component by way of the outlet, wherein the arced pathway loops back over itself in a radial direction in a plane perpendicular to the axial-radial plane, the leakage area located between adjacent shrouds of the plurality of adjacent turbomachine buckets; and
a hot gas path between adjacent airfoils of the adjacent turbomachine buckets, wherein the hot gas path is distinct from the leakage area.
10. The set of turbomachine buckets of claim 9 , wherein each of the shrouds includes a circumferentially facing edge facing a circumferentially facing edge of the adjacent shroud, wherein the arced pathway includes at least one outlet or inlet at the circumferentially facing edge.
11. The set of turbomachine buckets of claim 9 , wherein the arced pathway includes a series of intersecting plenums for allowing flow of the coolant to loop back over the leakage area.
12. The set of turbomachine buckets of claim 9 , wherein the arced pathway loops back over itself to direct the portion of the coolant to the leakage area.