Patent ID: 6927361
Filing Date: 2005-08-09
Classification: B23K,C21D,C23C

Abstract:
1. A welding process for an aircraft engine article comprising the steps of: providing at least two assemblies to be welded together to form a unitary article, said assemblies each having a faying surface and a face side, said assemblies each comprising a superalloy selected from the group consisting of iron-based superalloys and nickel-based superalloys; heating the assemblies in an oxidative atmosphere, at a rate to minimize distortion of the assemblies, to a temperature in a range of about 1400° F. to about 2000° F.; holding the assemblies at a temperature in the range of about 1400° F. to about 2000° F. for a preselected time sufficient to form an oxide layer of a preselected thickness on at least the face side of the assemblies; cooling the assemblies to ambient temperature; providing at least the faying surfaces of the assemblies substantially free of an oxide layer, while providing the face sides of the assemblies with an oxide layer of a preselected thickness range; forming a weld joint by placing the assemblies so that their faying surfaces are opposed; welding the assemblies using a gas tungsten arc process to form a unitary article; resolutioning and stress relieving the article in a non-oxidative atmosphere to relieve stress in the article; and cooling the article to ambient temperature.