Hot gas path component and methods of manufacture
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 method comprising:
forging or casting a first portion of a turbomachine component, the first portion including at least one of a stainless steel or an alloy steel;
additively manufacturing a second portion of the turbomachine component, the second portion including a nickel alloy, the additively manufacturing of the second portion of the turbomachine component including forming an arced cooling feature within the second portion, the arced cooling feature having an outlet, the second portion formed of a material having a thermal expansion coefficient differing by 5 percent to 25 percent from a thermal expansion coefficient of the first portion, wherein the second portion has 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 cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component by way of the outlet, wherein the arced cooling feature loops back over itself in a radial direction in a plane perpendicular to the axial-radial plane; and
joining the second portion to the first portion.
2. The method of claim 1 , wherein the forging or casting of the first portion includes forging or casting from at least one of a stainless steel or an alloy steel.
3. The method of claim 1 , wherein the additively manufacturing includes three-dimensionally printing the second portion of the turbomachine component.
4. The method of claim 1 , wherein the joining includes welding or brazing the second portion to the first portion.
5. The method of claim 1 , wherein the first portion and the second portion collectively form a gas turbine shroud after the joining.
6. The method of claim 5 , further comprising joining the gas turbine shroud to a turbomachine airfoil.
7. A method comprising:
additively manufacturing a section of a turbomachine component using a base material including a nickel alloy, the additively manufacturing of the section of the turbomachine component including forming an arced cooling feature within the section, the arced cooling feature having an outlet, wherein the arced cooling feature is located within the section to direct a portion of a coolant to a leakage area of the turbomachine component by way of the outlet, wherein the arced cooling feature loops back over itself in a radial direction in a plane perpendicular to the axial-radial plane, wherein the section of the turbomachine component has 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
joining the section of the turbomachine component to a preformed base section of the turbomachine component,
wherein a thermal expansion coefficient of the section of the turbomachine component differs by less than 25 percent from a thermal expansion coefficient of the preformed base section.
8. The method of claim 7 , further comprising forging or casting the preformed base portion from at least one of a stainless steel or an alloy steel prior to the additively manufacturing of the section of the turbomachine component.
9. The method of claim 7 , wherein the additively manufacturing includes three-dimensionally printing the section of the turbomachine component.
10. The method of claim 7 , wherein the joining includes welding or brazing the section of the turbomachine component to the preformed base section of the turbomachine component.
11. The method of claim 7 , wherein the joined section and the base section collectively form a gas turbine shroud, the method further comprising bonding the gas turbine shroud to a turbomachine airfoil.