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本文研究了四种航空发动涡轮盘高温合金的低循环应变疲劳性能,结果表明,在600、650℃空气介质中,当总应变范围Δε_T<1.51%时,GH132合金的疲劳性能优于GH36合金;600、700℃下,GH33A优于GH33合金。GH36表现为循环硬化;GH132基本属循环软化;GH33和GH33A合金出现多次循环硬化-软化现象。所有合金的Δε_T-N_f关系曲线在双对数坐标中呈线性关系,其高温低循环应变疲劳寿命可以Δε_TN_f~α=C方程来估算。
The fatigue behavior of four kinds of aero-engine turbine disk superalloys at low cyclic strain was studied. The results show that the fatigue performance of GH132 alloy is better than that of GH36 alloy when the total strain range Δε_T <1.51% in air medium at 600 and 650 ℃. At 600,700 ° C, GH33A is superior to GH33 alloy. GH36 showed cyclic hardening; GH132 is the basic cycle of softening; GH33 and GH33A alloy appeared multiple cycles of hardening - softening phenomenon. The Δε_T-N_f relation curves of all the alloys show a linear relationship in the logarithmic coordinates. The fatigue life under high temperature and low cyclic strain can be estimated by Δε_TN_f ~ α = C equation.