Patent ID: 6468040
Filing Date: 2002-10-22
Classification: F01D,F05D,Y10T

Abstract:
A new airfoil for use in a gas turbine engine, comprising:an airfoil cast of a first superalloy material having a predetermined high temperature strength and oxidation resistance and having a predetermined length extending from a dovetail end to a tip end; and a squealer tip made of a Reneâ€² 142 material having resistance to high temperature oxidation of a preselected height attached to the tip end of the airfoil casting and extending away from the tip end, the Reneâ€² 142 material having a predetermined high temperature strength greater than the high temperature strength of the first superalloy material and oxidation resistance greater than the oxidation resistance of the first superalloy material; and the airfoil and attached squealer tip having an overall length within predetermined design requirements for the airfoil.