发明名称 High-temperature alloy for gas turbine moto - rs
摘要 <p>The alloy is processed while compressed at a temp. below, but within approx. 250 degrees C of its normal recrystallisation temp. The alloy is then forged into the shape required at a temp. within approx. 194 degrees C, but not above the alloy's normal recrystallization temp. Finally the forged alloy is heat treated to return it to its normal state of high strength and hardness. Specif. the processed material is a precipation-hardened Ni and Ti alloy billet consisting of sintered power.</p>
申请公布号 FR2040179(A1) 申请公布日期 1971.01.22
申请号 FR19690009956 申请日期 1969.04.11
申请人 UNITED AIRCRAFT CORP 发明人
分类号 C22F1/00;(IPC1-7):21J1/00;22F1/00;02C7/00 主分类号 C22F1/00
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