• CN:11-2187/TH
  • ISSN:0577-6686

›› 2013, Vol. 49 ›› Issue (10): 116-126.

• 论文 • 上一篇    下一篇

航空发动机涡轮盘用GH4133B合金疲劳裂纹萌生与短裂纹扩展研究

赵荣国;李红超; 蒋永洲; 谭敦厚;李俊斐;罗希延   

  1. 湘潭大学土木工程与力学学院;空军航空大学航空理论系;中国航空工业集团黎阳航空发动机公司
  • 发布日期:2013-05-20

Research on Fatigue Crack Initiation and Short Crack Propagation of GH4133B Superalloy Used in Turbine Disk of Aero-engine

ZHAO Rongguo;LI Hongchao;JIANG Yongzhou;TAN Dunhou;LI Junfei;LUO Xiyan   

  1. College of Civil Engineering and Mechanics, Xiangtan University Department of Aviation Theory, Air Force Aviation University Liyang Aero-Engine Corporation, Aviation Industry Corporation of China
  • Published:2013-05-20

摘要: 疲劳裂纹萌生与短裂纹扩展研究是航空发动机构件损伤容限设计的关键和基础。针对航空发动机涡轮盘用GH4133B合金,开展室温下不同缺口半径、不同应力比的疲劳裂纹萌生和短裂纹扩展研究,结果表明控制参量ΔKI/(r)0.5可较好地表征疲劳裂纹萌生寿命,且随控制参量值的增大,缺口半径对疲劳裂纹萌生寿命的影响增大,而疲劳裂纹萌生寿命随应力比的增大呈先增后减趋势。采用有效应力强度因子范围ΔKeff,能较好地描述短裂纹扩展速率随裂纹扩展先减速后加速的特性。疲劳失效断口的扫描电镜观测表明,短裂纹扩展区的放射性条纹之间存在解理台阶,且解理台阶上有早期疲劳条带,从而从断裂表面形貌分析角度,揭示了GH4133B合金在疲劳裂纹扩展初期速率较高,而后扩展速率逐渐下降的短裂纹扩展微观机理。

关键词: 短裂纹扩展, 断口分析, 疲劳裂纹萌生, 涡轮盘, 应力比

Abstract: Fatigue crack initiation and short crack propagation is the key and foundation of damage tolerance design of aero-engine components. The researches on fatigue crack initiation and short crack propagation under different notch radii and stress ratios for GH4133B superalloy used in turbine disk of aero-engine are carried out at ambient temperature. It is shown that a control parameterΔKI/(r)0.5 can be used to characterize the fatigue crack initiation life, and the effect of notch radius on fatigue crack initiation life increases with increasing control parameter, while the fatigue crack initiation life firstly increases and then decreases with increasing stress ratio. An effective stress intensity factor range ΔKeff, can be adopted to describe the deceleration and acceleration of crack growth rate during the short crack propagation. The fatigue fracture surface morphologies are investigated using scanning electron microscopy. It is shown that there is a cleavage step between two adjacent radial stripes, and a series of early fatigue striations exist on the cleavage step, which reveals the microscopic mechanism of short crack propagation from the point of view of fracture surface morphology that the fatigue crack growth rate is intially higher, and then gradually decreases with the propagation of short crack.

Key words: Fatigue crack initiation, Fractrography, Short crack propagation, Stress ratio, Turbine disk

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