Method to Produce Titanium Metal Matrix Composites with Improved Fracture and Creep Resistance.
Patent, Filed 1 Feb 88, patented 18 Apr 89,
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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A method for improving the microstructure of consolidated titanium alloy metal matrix composites which comprises the steps of a heating the composite to a temperature in the range of 800 deg to 2000 deg F., the temperature being below the temperature at which interfacial reactions occur between the metal matrix and the fiber, and diffusing hydrogen into the composite to achieve a hydrogen level of about 0.50 to 1.50 weight percent b altering the temperature of the composite to a transformation temperature at or near the temperature of transformation of HCP alpha in the hydrogenated composite to BCC beta c cooling the composite to room temperature d heating the thus-cooled composite to a temperature below the transformation temperature, and diffusing hydrogen out from the composite and e cooling the composite to room temperature. PAT-CL-148-127. jes
- Laminates and Composite Materials