一种高性能航空涡轮盘用铸锻合金的研究进展
网络出版日期: 2015-09-08
基金资助
*国家自然科学基金项目51171179, 51271174, 51331005, 51401071和11332010资助
RESEARCH PROGRESS IN A HIGH PERFORMANCE CAST & WROUGHT SUPERALLOY FOR TURBINE DISC APPLICATIONS
Online published: 2015-09-08
Supported by
Supported by National Natural Science Foundation of China (Nos.51171179, 51271174, 51331005, 51401071 and 11332010)
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.
谷月峰,崔传勇,袁勇,钟志宏 . 一种高性能航空涡轮盘用铸锻合金的研究进展[J]. 金属学报, 2015 , 51(10) : 1191 -1206 . DOI: 10.11900/0412.1961.2015.00442
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