烧结温度对SiO<sub>2</sub>-ZrO<sub>2</sub>体系陶瓷型芯材料性能影响研究

刘晓光; 齐长见; 贺莉丽; 唐定中; 肖程波; 姚建省; 顾国红; 李鑫

烧结温度对SiO₂-ZrO₂体系陶瓷型芯材料性能影响研究

1.
北京航空材料研究院先进高温结构材料国防科技重点实验室,北京,100095;
2.
中航工业南方航空工业集团有限公司,湖南,株洲,412002;
3.
天津大学材料科学与工程系,天津,300072

基金项目:

国防科工局基础科研项目(B0520060458)

详细信息

作者简介:
刘晓光(1976- ),男,博士,高级工程师,陶瓷材料专业研究,(E-mail)xiaogliu@sina.com.

中图分类号: TG132.3
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出版历程
- 刊出日期: 2011-10-01

Effect of Sintering Temperature on Ceramic Cores Performances of SiO₂-ZrO₂ system

1.
Beijing Institute of Aeronautic Materials,Beijing 100095,China;
2.
Avic South Aviation Industry Limitied Corporation,Zhuzhou 412002,Hunan China;
3.
Tianjin University,Tianjin 300072,China

摘要

摘要: 采用传统的热压铸工艺制备可快速脱芯的定向、单晶空心涡轮叶片用SiO2-ZrO2体系陶瓷型芯材料,研究结果表明,该材料随烧结温度从1150℃增加到1200℃,收缩率变大,当烧结温度超过1200℃时,烧结收缩增加显著,1200℃烧结的陶瓷型芯晶粒发育比较完善,主要相组成为非晶SiO2、方石英、ZrO2,其综合性能最佳,室温强度可达42.9 MPa,1550℃具有较好的抗高温变形性和优异的高温强度,高温变形为0.1mm,高温强度可达27.9MPa,开气孔率可达30.4%,体积密度为1.92g/cm3,烧结收缩率仅为0.4%,方石英析出量20%左右,能够满足我国航空发动机高温合金空心涡轮叶片的浇注要求.
- 热压铸 /
- 空心叶片 /
- 陶瓷型芯 /
- 发动机 /
- 高温合金
Abstract: The easy leachable SiO2-ZrO2 ceramic cores used in directional solidification and single crystal hollow blades were prepared by traditional hot-pressure casting.The results show that the a sintering shrinkage increased with the increasing sintering temperature from 1150℃ to 1250℃,and sintering shrinkage is increased markedly above 1200℃.Well-grown crystalline grains were shown,and main compositions are composed with non-crystal silica,cristobalite and zirconia.The material properties sintering at 1200℃ are optimized,and bending strengths reach 42.9MPa,and best anti-deformation and bending strengths are also obtained at 1550℃.High temperature anti-deformation is 0.1mm,and the high temperature bending strength,pore,densiy and sintering shrinkage are 27.9MPa,30.4%,1.92g/cm3 and 0.4% respectively.The formations of cristobalite is about 20%.It meets the pouring requirement for superallay hollow turbine blades of the aero-engine.
- hot-pressure casting /
- hollow blades /
- ceramic cores /
- engine /
- superalloy

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参考文献(12)

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