Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen

LI Quan-tong; TONG Xu-dong; GAO Xing-wei; CHEN Wei; CHENG Li

doi:10.13224/j.cnki.jasp.2014.10.026

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Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen

更新时间：2026-07-07

- Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen
- Issue 10, (2014)
- 作者机构：
  
  空军工程大学航空航天工程学院,西安,710038
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.10.026
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
李全通, 通旭东, 高星伟, 陈卫, 程礼. 基于试片超高周疲劳试验的叶片高周疲劳寿命估算方法[J]. 航空动力学报, 2014, (10): 2471-2475. doi: 10.13224/j.cnki.jasp.2014.10.026

LI Quan-tong, TONG Xu-dong, GAO Xing-wei, et al. Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen[J]. 2014, (10).
李全通, 通旭东, 高星伟, 陈卫, 程礼. 基于试片超高周疲劳试验的叶片高周疲劳寿命估算方法[J]. 航空动力学报, 2014, (10): 2471-2475. doi: 10.13224/j.cnki.jasp.2014.10.026 DOI：

LI Quan-tong, TONG Xu-dong, GAO Xing-wei, et al. Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen[J]. 2014, (10). DOI： 10.13224/j.cnki.jasp.2014.10.026.

摘要

依据梁的振动理论，推导了叶尖振幅a与叶片自振频率f乘积af值，来表征叶片振动应力；基于某型航空发动机压气机叶片材料试片超高周疲劳试验结果，结合af值理论，推断该叶片高周疲劳寿命.对该叶片进行1阶弯曲高周疲劳试验，结果显示：af值为1700，1800，1900mm/s时，超高周试验疲劳试片和实际叶片的疲劳寿命均在1×107，0.7×107，0.5×107周次附近，即超高周疲劳试验试片和实际叶片的疲劳寿命基本一致.

Abstract

According to girder vibration theory of beam

"af"value

which is the product of blade tip vibration amplitude "a" and frequency "f"

was deduced to express vibration stress of blade. Based on the ultra-high cycle fatigue test result of a type of aero-engine compressor blade material specimen and "af" value theory

the blade high cycle fatigue life was deduced. The results of blade first order bending high cycle fatigue validated the deduction. It shows that when "af" value is 1700

1800

1900mm/s

the fatigue lives of ultra-high cycle fatigue test specimen and actual blade are in the vicinity of 1×107

0.7×107 and 0.5×107 cycle

indicating the fatigue life of ultra-high cycle fatigue test specimen is consistent with the actual blade.

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Related Institution

Shenyang Engine Research Institute，Aero Engine Corporation of China

重庆大学航空航天学院

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先进航空发动机协同创新中心

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