GH2132航空发动机涡轮盘-现货价格--午虎钢研技术 航空发动机涡轮盘用GH2132 GH2132是Fe-25Ni-15Cr基高温合金，加入钼、钛、铝、钒及微量硼综合强化。在650℃一下具有高的屈服强度和持久、蠕变强度，并具有较好的加工塑性和满意的焊接性能。适合制造在650℃以下长期工作的高温承力部件。 Ø 化学成分 元素 C Cr Ni Mo Ti Fe V W/% ≤0.08 13.5-16.0 24.0-27.0 1.0-1.5 1.75-2.30 余 0.10-0.50 B Mn Al Si P S 0.001-0.010 1.00-2.00 不大于 0.40 1.00 0.030 0.020 Ø 热导率 温度/℃ 100 200 300 400 500 600 700 800 热导率/（w/m.c） 14.2 15.9 17.2 18.8 20.5 22.2 23.9 25.5 Ø 线膨胀系数 温度/℃ 20-100 20-200 20-300 20-400 20-500 20-600 20-700 膨胀系数/10-6c-1 15.7 16.0 16.5 16.8 17.3 17.5 17.9 Ø 力学性能 标准热处理制度：℃，1-2h，油冷+℃，12-16h，空冷 指标 σb/MPa σ0.2/MPa δ5/% Ψ/% Aku/kJ/m2 HBS 室温性能 不小于 910 930 20 40 550℃ 785 16 28 810 - 650℃ 735 15 20 790 - Aerospace turbine disc. Aircraft engine turbine disk in GH2132. GH2132 is a high-temperature alloy of fe-25ni-15cr, which is combined with molybdenum, titanium, aluminum, vanadium and trace boron. At 650 ℃ has high yield strength and lasting and creep strength, and has good processing plastic and satisfactory welding performance. Suitable for manufacturing in the long-term work under 650 ℃ high temperature bearing parts. Ø chemical composition Element C Cr Ni Mo Ti Fe V. W / % acuities were 0.08 13.5 16.0 24.0 27.0 13.5 16.0 1.75 2.30 0.10 0.50 B Mn Al Si P S No greater than 0.001-0.010 1.00-2.00. 0.40 1.00 0.030 0.020 Ø thermal conductivity Temperature / ℃ 100 200 300 400 500 600 700 800 Thermal conductivity (w/m.c) 14.2 15.9 17.2 18.8 15.9 22.2 23.9 25.5 Ø linear expansion coefficient of Temperature / ℃ Expansion coefficient /10-6c-1 15.7 16.0 16.5 16.8 17.3 17.5 17.9. Ø mechanical properties Standard heat treatment system: ℃, 1 to 2 h, oil cooling + ℃, 12-16 h, air cooling / MPa delta sigma b/MPa sigma 0.2 Ψ / 5 / % % Aku/kJ/m2 HBS The room temperature performance is not less than 910 . 930 20 to 40 550 ℃ 785 28 810-16 650 ℃ 735 15 790-20
