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一种高性能航空涡轮盘用铸锻合金的研究进展

RESEARCH PROGRESS IN A HIGH PERFORMANCE CAST & WROUGHT SUPERALLOY FOR TURBINE DISC APPLICATIONS

中文摘要英文摘要

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.

he advanced cast & wrought (C&W) superalloys for turbine disc applications have low temperature bearing capacity and poor processing ability compared with the powder metallurgy (PM) superalloys. Recently,a new kind of C&W Ni-Co base disc superalloys, named as TMW alloy, has been developed on the basis of an innovative concept. Full-scale pancakes (440 mm in diameter and 65 mm in thickness) with an average grain size of about 10 mm were successfully manufactured by a conventional C&W processing route. TMW alloys can provide 58~76 temperature advantages over alloy U720Li in 0.2% creep strain life under 630 MPa and are comparable with the advanced PM disc superalloys. In this work, the alloy design, preparation processing capacity, microstructural control, performance characteristics and deformation strengthening mechanisms were briefly introduced.

袁勇、谷月峰、钟志宏、崔传勇

10.12074/202303.00559V1

航空航天技术冶金技术

铸锻高温合金TMW合金合金设计组织控制变形机理

袁勇,谷月峰,钟志宏,崔传勇.一种高性能航空涡轮盘用铸锻合金的研究进展[EB/OL].(2023-03-19)[2025-08-02].https://chinaxiv.org/abs/202303.00559.点此复制

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