| US H2,227 H1 | ||
| High speed titanium alloy microstructural conversion method | ||
| Seshacharyulu Tamirisakandala, Beavercreek, Ohio (US); Prasad VRK Yellapregada, Bangalore (India); Steven C. Medeiros, Beavercreek, Ohio (US); William G. Frazier, Oxford, Miss. (US); and James C. Malas, Bellbrook, Ohio (US) | ||
| Assigned to The United States of America as represented by the Secretary of the Air Force, Washington, D.C. (US) | ||
| Filed on Nov. 13, 2002, as Appl. No. 10/295,550. | ||
| Claims priority of provisional application 60/356040, filed on Feb. 11, 2002. | ||
| Int. Cl. C22F 1/18 (2006.01) | ||
| U.S. Cl. 148—671 | 3 Claims |
| 1. A method of converting a Ti—6 Al—4V alloy material microstructure from lamellar to equiaxed, comprising the steps of:
providing a lamellar microstruure Ti—6Al—4V alloy material;
processing said material in such manner to convert the microstructure thereof from lamellar to equiaxed, said processing step
including the step of;
estimating an average high strain rate for said material;
estimating an adiabatic temperature rise within said material as a result of deformation at said strain rate;
determining the effect of chemical composition of said material upon the β transus temperature;
estimating a deformation temperature by incorporating said adiabatic temperature rise from said adiabatic temperature rise
estimating step above and incorporating the effect of chemical composition from said determining step above such that the
temperature of the material is within the range of about 975-1010° C., said deformation temperature further being chosen such
that the β transus temperature is not exceeded at any location within said material;
heating said material to the temperature obtained from said deformation temperature estimating step above; and,
extruding said material at a rate obtained from said strain rate estimating step above.
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