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AssigneeGeneral Electric Company
InventorsWilliam Henry Harrison, Thomas Joseph Kelly, Michael James Weimer
Estimating the term…
A heat treatment process that will restore the mechanical properties of an aircraft engine article that includes a cast Inconel 718 portion welded to a wrought portion. The heat treatment process includes placing an article that includes the Inconel 718 cast portion into a heat treatment chamber, evacuating the chamber to a suitable atmosphere, heating the chamber in a manner that minimizes distortion of the cast portion to a temperature in the range of 1950° F. to 2050° F., holding the temperature in that range for a period of time sufficient to solution all the delta phase precipitates, and then cooling the article to room temperature in a manner that minimizes distortion of the article. After solution heat treatment, the wrought portion of the engine part can be removed and replaced and the engine article can be reprocessed.
A heat treatment process for restoring the properties of an aircraft engine article having an Inconel 718 cast portion and a forged portion that has been subjected to repeated thermal cycles below the δ solvus comprising the steps of:
An aircraft engine frame comprising a cast Inconel 718 portion and a wrought Inconel 718 portion treated with the process of step 1.
A aircraft engine frame comprising a cast Inconel 718 portion and a wrought Waspaloy portion treated with the process of step 1.
Dependencies are inferred from the claim text.