Patent ID: 8876992
Filing Date: 2014-11-04
Classification: B21J,B21K,B23H,B23P,C22B,C22C,C22F

Abstract:
1. A process for manufacturing a turbine engine component comprising the steps of: casting ingots made of a gamma TiAl material using a double vacuum arc remelting casting technique; subjecting said cast ingots to a hot isostatic pressing to close porosity; forming at least one pancake of said gamma TiAl material by isothermally forging the hot isostatic pressed ingots; performing said isothermal forging step at a temperature in the range of from 1850° F. to 2200° F. using a strain rate in the range of from 0.015/min to 0.6/min; sectioning each said pancake into a plurality of blanks; heat treating said blanks to produce a desired microstructure and mechanical properties, wherein said heat treating step comprises subjecting each said blank to a first heat treatment at a temperature in the range of from 2200° F. to 2300° F. for a time period in the range of from one hour to two hours, air cooling each said blank, and then subjecting each said blank to a second heat treatment at a temperature in the range of from 1550° F. to 1700° F. for a time period in the range of from four to six hours and furnace cooling each said blank to room temperature; and machining the blanks into finished turbine engine components.