Patent ID: 9393620
Filing Date: 2016-07-19
CPC Classification: B22F,B33Y,Y02P,Y10T

Claim Text:
1. A method of making a turbine section component of a gas turbine engine, the method comprising: forming the component by additive manufacturing using superalloy powder to form the component with internal cooling passages located proximate an exterior surface of the component, at least some of the internal cooling passages within 0.050 inches to 0.010 inches of the exterior surface; hot isostatic pressing the part to enhance mechanical properties, producing an initial plurality of grains resulting in an equiaxed grain structure in the part; directional recrystallizing the part to introduce a directional grain structure and reduce the initial plurality of grains to a final plurality of directional grains in the part; forming a bond coat on the surface; and depositing a thermal barrier layer on the bond coat; wherein a number of the final plurality of directional grains is less than 30.