摘要
本文对试车150小时定向凝固 DZ38G 合金高压Ⅱ级涡轮叶片进行解剖分析,其中包括宏观检查、显微组织和防护涂层分析。该()片试车后无任何损伤和裂纹,表面涂层完好。合金中晶界和γ′相无明显变化,但共晶发生部分溶解,MC 碳化物周围有 M_(23)C_6分解物,涂层微观组织有氧化腐蚀现象。试车前、后叶片硬度值基本在同一水平。
This paper presents an examination and analysis of Ⅱ stage turbine-blade of directionally solidified alloy after operating 150 hours.It has been found that there are no damages and cracks,the coating layer is also perfect at macro-scale. Examinations at micro-scale show that there is no change with grain boundries and γ′-precipitates.However,eutectic has been found to dissoluted partly and carbides M_(23)C_6 have been observed surrounding the MC.Oxidation and corrosion have been found to occur on the coating.The value in hardness is almost the same before and after operating
出处
《航空材料学报》
EI
CAS
CSCD
1991年第2期26-32,共7页
Journal of Aeronautical Materials
基金
国家自然科学基金资助
