摘要
针对服役涡轮叶片的疲劳性能及寿命评估问题,发展了一种适用于含薄壁和内冷通道等复杂结构特征涡轮叶片的小尺寸试样取样技术及小试样的高温疲劳试验夹持方法。应用该方法对不同大修间隔的某型航空发动机第1级高压转子涡轮叶片进行了取样,对叶片取样小尺寸试样在850℃下开展疲劳试验。试验结果表明:所发展的复杂构型涡轮叶片取样技术和小尺寸试样高温疲劳夹持方法能够有效应用于该型服役发动机高压涡轮叶片的取样疲劳性能试验;真实服役的涡轮叶片小试样的疲劳性能与标准热处理状态合金的相比出现了劣化,并且随着服役时间的延长劣化程度加剧,寿命降缩短例最大超过90%;服役涡轮叶片取样小试样的疲劳裂纹主要萌生于表面和亚表面的缺陷,共晶组织和碳化物是服役涡轮叶片裂纹萌生的危险位置。
In order to carry out fatigue property assessment of service turbine blades,a small-size coupon sampling and fatigue test method for small samples of turbine blades with complex structural features such as thin walls and internal cooling channels were developed. This method was used to sample the first-stage high-pressure rotor turbine blades of an aeroengine with different overhaul intervals.Fatigue experiments were then performed on small samples of blades at 850 ℃. The experimental results show that,for the real service,the fatigue performance of the small samples are also deteriorated compared with the alloy samples in the standard heat treatment state and the deterioration intensifies with the increase of the service time. The maximum reduction of fatigue life is over 90%. The fatigue cracks originated mainly from surface and subsurface defects. Eutectic structures and carbides are dangerous positions for crack initiation in service turbine blades.
作者
范永升
杨晓光
王相平
石多奇
王良
王鹏
FAN Yong-sheng;YANG Xiao-guang;WANG Xiang-ping;SHI Duo-qi;WANG Liang;WANG Peng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Beijing Key Laboratory of Aeroengine Struc-ture and Strength,Beijing 100191,China;AECC Shenyang Engine Research Institute,Shenyang,110015,China;Chengdu Holy In-dustry&Commerce Corp.LTD,Chengdu 611936,China;Beijing Institute of Space Launch Technology,Beijing 100076,China)
出处
《航空发动机》
北大核心
2022年第2期114-120,共7页
Aeroengine
基金
国家科技重大专项(2019-IV-0017-0085)资助。
关键词
涡轮叶片
小试样
取样
失效机理
高温疲劳
夹持方法
航空发动机
turbine blades
small coupons
sampling
failure mechanism
fatigue at high temperature
camping method
aeroengine
