某航空发动机用GH738材料热处理工艺探讨

Heat Treatment of Aircraft Meterial GH738

GH738是以γ′相沉淀硬化的镍基高温合金,为航空发动机高温紧固件用料[1]。目前采用的热处理工艺为:固溶,1020℃/4 h/油冷;时效,850℃/4 h/通氩气开风扇冷却,760℃/16 h/通氩气开风扇冷。在此工艺下,时常出现零件硬度偏高、高温持久性能偏低等质量问题。通过对GH738进行大量的热处理工艺试验及试验数据分析,表明该材料在:固溶1040℃/4 h/油冷、时效850℃/4 h/通氩气开风扇冷却、760℃/16 h/通氩气开风扇冷的工艺路线下,所获得的零件强度、硬度和高温持久性能符合相应标准[2],稳定性好,满足了实际生产要求,为航机生产提供了更为合理的热处理工艺方法。

GH738 is a nickel-high-temperature alloy of precipitation-heading as γ′phase, and it is used for the high temperature fastener of aero-engine. The present art is aged at 850 ℃ for 4 h and cooled in argion by flow fan and aged at 760 ℃ for 16 h and cooled in argon by flow fan, after solutoning at 1020 ℃ for 4 h and cooled in oil. The process is always excessive hardness and low persistent at high temperature. We do many experiments of GH738, and the experiment results show that parts＇ strength, hardness, and persistent property at high temperature is satisfactory ,and the present process is aged at 850℃ for 4 h and cooled in argon and aged at 760℃ for 16 h and cooled in argon by flow fan, after solution at 1040℃ for 4 h and cooled in oil. The measurement of these samples fits quit well with others. It meets the requirements for actual production, and it supplies proper method for aero-engine production.