兹将苏联在航空用变形高温合金领域的进展情况图示于后,供参考。制作发动机涡轮工作叶片用的镍基棒材合金,见图1a——各合金在950℃时,100小时持久强度值和图16—20 Rrc/MM~2持久强度下,各合金的工作温度。制作发动机燃烧室和加力燃烧室系统 The United States hereby shows the progress of the Soviet Union in the field of aviation deformation superalloys for reference. Figure 1a shows the operating temperature of each alloy at 950 ° C for 100 hours and Figure 16-20 Rrc / MM ~ 2 long-term strength for all nickel-based bars made of engine turbine working blades. Production of engine combustion chamber and afterburner system