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针对航空涡轮盘用先进铸锻变形高温合金热加工难、承温能力低于680℃(630 MPa,1000 h持久寿命)、难以满足现代航空发动机设计需求等不足,提出了优化析出强化相成分和引入微孪晶以提高合金中温区(合金服役温区)强度、同时减弱析出相高温强化效果和固溶温度以降低合金高温区(合金加工温区)强度的理念,设计并制备出系列Ni-Co基铸锻高温合金(TMW合金).设计合金盘坯(直径440 mm,厚65 mm)的制备和性能测试表明,TMW合金可在常规熔铸和锻造设备上热加工制备,承温能力超过700℃,比目前最强的商用铸锻涡轮盘合金U720Li提高了50℃以上.从TMW合金的设计思想、成分特点、锻造加工性、组织控制、性能特征和变形强化机理等方面,简要介绍了这种高性能铸锻变形高温合金的主要研究进展.
Aiming at the shortcomings of the heat treatment of the advanced forging deformation superalloy for aviation turbine disk, the capability of bearing temperature below 680 ℃ (630 MPa, 1000 h long life), it is difficult to meet the design requirements of modern aeroengine. The introduction of micro-twins to improve the strength of the alloy in the temperature zone (alloy service temperature zone), while reducing the precipitating phase high temperature strengthening effect and solution temperature to reduce the alloy high temperature zone (alloy processing temperature) strength concept, design and preparation of a series of Ni- Co-based forging superalloys (TMW alloys). The preparation and performance tests of designed alloy disk blanks (diameter 440 mm, thickness 65 mm) show that TMW alloys can be hot-worked on conventional casting and forging equipment with a temperature tolerance of over 700 ℃, which is 50 ℃ higher than that of U720Li, which is the strongest commercial cast-forged turbine disk alloy.According to the design concept, compositional characteristics, forging processability, organization control, performance characteristics and deformation strengthening mechanism of TMW alloy, Main research progresses of high performance forging deformation superalloy.