Airfoil with sintered powder components
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsMatthew T. Kush, Michael Wood, Scott Nelson, Joseph Peter Henderkott
Life of this patent
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Abstract
A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.
Claims15
A method for forming a component for a gas turbine engine, the method comprising:
- forming a first portion of the component, wherein the first portion comprises a cast metal or metal alloy;
- forming a second portion of the component, wherein the second portion comprises a presintered preform defining at least one support structure, wherein the presintered preform includes a partially sintered mixture of high-melt metal alloy particles and low-melt braze material particles;
- positioning the second portion on the first portion to define an assembly, wherein the first portion and the second portion define at least one cooling channel therebetween;
- and
- heating the assembly to join the first portion and the second portion and form the component,
- wherein the component comprises a radial turbine blade, wherein the first portion comprises a hub and a first part of a plurality of airfoils of the radial turbine blade, and wherein the second portion comprises a plurality of second parts of the plurality of airfoils.
Dependencies are inferred from the claim text.