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试验研究了既保证钛铝合金涡轮叶片成形又能形成择优取向层片组织的型壳预热温度范围,并用铸造板片模拟叶片组织,通过测试抗弯强度和缺口拉伸性能对其可靠性进行评价。结果表明,在一定的浇注熔体温度下,型壳预热温度在400~600℃,钛铝合金涡轮既能充型完整,又能保证叶片中层片取向平行于表面;模拟板片中形成的有取向层片组织具有更好的抗弯强度,有利于提高涡轮叶片抗异物冲击的能力;具有择优取向层片组织模拟板片的标准缺口试样的抗拉强度大于光滑试样,说明涡轮叶片抗损伤能力强。
The experimental preheating temperature range of the shell which not only ensures the formation of titanium-aluminum alloy turbine blades but also forms the preferred oriented lamellar structure is studied. The leaf structure is simulated by the cast slab, and the reliability is tested by testing the flexural strength and notched tensile properties Evaluation. The results show that under certain pouring melt temperature, the shell preheating temperature is between 400 ℃ and 600 ℃, the titanium aluminum alloy turbine can not only complete the filling but also ensure that the blade midpair is oriented parallel to the surface. Oriented lamellar structure has better flexural strength, which is beneficial to improve the ability of turbine blades to resist the impact of foreign objects. The tensile strength of standard notched specimens with preferential oriented lamellar tissue simulated plates is larger than that of smooth samples, Anti-damage ability.