摘要
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 casting shell preheating temperature ranges were studied,in which the lamellar microstructure with preferred orientation in TiAl based turbine blades could be obtained,and the reliability of the turbine blades was evaluated by testing the bending properties and room temperature notch tensile properties of the simulated plate.It was found that,at a pouring of certain temperature,the preheat temperature range of shell was 400~600 ℃ for complete filling up the mould of the Ti-Al based turbine blades and ensuring the lamellar orientation in the blades parallel to the casting surface.The mechanical properties testing results of the plate show that the preferred orientated lamellar structure obtained in the plate performances better bending properties,which is beneficial to impact resistance of the turbine blades;the standard notched specimen exhibit higher ultimate tensile strength than that of un-notched specimen,which indicates that turbine blades possess good damage resistance.
出处
《铸造技术》
CAS
北大核心
2011年第8期1075-1077,共3页
Foundry Technology
关键词
钛铝合金增压涡轮
择优取向层片组织
弯曲强度
缺口拉伸性能
Turbine wheels of Ti-Al based alloy
Lamellar microstructure with preferred orientation
Bending strength
Notched tensile properties
