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The increase in aircraft engine thrust has required that main engine shaft material exhibit improved tensile strength and cyclic capability. The application of a "Direct Age" heat treatment to a controlled GFM fine grain billet process is discussed. "Direct Aged" tensile and low cycle fatigue properties are presented and compared to fine grain solution and aged material. Improvements in tensile properties were noted at temperatures up to 1200F with the largest improvement occurring at the bar surface. No difference in microstructure or properties was noted along the bar when bars were limited to less than 30' in length. Longitudinal properties were found to be slightly higher than those measured in the tangential direction. It is concluded that application of the "Direct Age" heat treatment to a controlled GFM ingot conversion practice can be used to improve Inconel 718 aircraft engine shaft properties. Superalloys 718,625 and Various Derivatives Edited by Edward A. Im-ia The Minerals, Metals & Materials Society, 1991

Rotary Forge Processing of Direct Aged Inconel 718 for Aircraft Engine Shafts