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| 1 | 薄壁结构高温随机振动疲劳寿命估算方法显示文摘为了研究涡轮转子叶片在高温环境中气流激振力作用下随机振动疲劳失效机理,从基础研究出发,采用薄壁板件为研究对象。基于高温试验台与振动台联合试验,结合数值仿真,得到了不同温度和不同振动量级组合下试验件根部与颈部的轴向动应力响应规律。基于疲劳累积损伤理论,采用改进的雨流计数法预估试验件的疲劳寿命。通过高温随机振动试验,同时参照常温随机振动试验,获得试验件在实际工况下的应力、应变、频率等动力学响应和寿命数据,并对各个试验组的响应与寿命进行数据统计,仿真与试验结果比较发现:数值仿真对试验件破坏位置判断准确,应力响应误差在5.6%以内,频率响应相差1%左右,疲劳寿命相差28.6%以内,证明了高温条件下随机振动疲劳分析方法是有效的而且精确的。 | 沙云东 朱付磊 赵奉同 张墨涵 | 2020 | 振动与冲击2020，39，2： | 7 |
| 2 | Out of phase thermal mechanical fatigue investigation of a directionally solidified superalloy DZ125显示文摘Out of phase(OP) thermal mechanical fatigue(TMF) behavior of a directionally solidified(DS) superalloy DZ125 was experimentally and numerically studied. Two different temperature conditions, which are 500–1000 °C and 400–900 °C, were considered in the present research.Stress and strain responses as well as fatigue life results were presented and discussed. Scanning electron microscope(SEM) and metallographic analysis were used to study the damage mechanism. An oxidation assisted crack initiation and propagation phenomenon were found to explain the shorted life under TMF cycles. In order to characterize the stress and strain deformations under TMF loadings, a modified Chaboche's constitutive model was applied. Additionally, the TMF life of the material was modeled and predicted by Neu–Sehitoglu damage law with high accuracy. | Hu Xiaoan Yang Xiaoguang Shi Duoqi Yu Huichen | 2016 | Chinese Journal of Aeronautics2016，29，1： | 3 |
| 3 | 涡轮叶片辐射热冲击疲劳试验控制技术研究及实现显示文摘针对涡轮叶片热冲击疲劳试验的加热模拟需求,采用了基于石英灯辐射加热与气化液氮和喷水强制冷却的多种方法。通过石英灯辐射加热系统、电动伺服装置和冷却装置的参与,实现了连续的热冲击和强制冷却降温过程。温度控制方法满足了辐射热冲击过程的快速升温要求,其与控制器直接输出驱动控制的分时联合应用,在强制冷却降温过程中避免了单纯温度控制所导致的加热系统高频次震荡现象。此方式为模拟涡轮叶片实际启动-停车循环的热冲击过程提供了新的思路和借鉴。 | 刘佳 田玉坤 宫永辉 何钦华 邱恒斌 | 2020 | 燃气涡轮试验与研究2020，33，2： | 3 |
| 4 | Stress-controlled LCF experiments and ratcheting behaviour simulation of a nickel-based single crystal superalloy with [001] orientation显示文摘Uniaxial ratcheting behaviour and low cycle fatigue(LCF)failure mechanism of nickel-based single crystal superalloy DD6 with[001]orientation are investigated through the stresscontrolled LCF tests with stress ratio of-1.Then the deformation behaviour during the wholelifetime from the beginning of the experiment to the fracture of the specimen,as well as the fractographic/metallographic morphology,are compared with the strain-controlled LCF experimental results.Through the scanning electron microscope(SEM)observations,it is shown that the failure characteristics under stress-controlled LCF loading are similar with those under strain-controlled loading.Nevertheless,unlike strain-controlled LCF loading,even under fully reversed cycle loading for stress-controlled LCF,DD6 shows significant ratcheting behaviour due to the tensioncompression asymmetry.In addition,the LCF lifetimes under stress control are significantly shorter than the LCF lifetimes under strain control,and the culprit might be the detrimental effect of ratcheting strain on LCF lifetime.Based on these phenomena,an improved crystal plasticity constitutive model on the basis of slip-based Walker constitutive model is developed through modifying the kinematic hardening rule in order to overcome the inaccurate prediction of decelerating stageand stable stage of ratcheting behaviour.Furthermore,combining the continuum damage mechanics,a damage-coupled crystal plasticity constitutive model is proposed to reflect the damage behaviour of DD6 and the accelerating stage of ratcheting behaviour.The simulation results for the stress-controlled LCF deformation behaviour including the whole-lifetime ratcheting behaviour show good agreement with the experimental data. | Bin ZHANG Rongqiao WANG Dianyin HU Kanghe JIANG Jianxing MAO Fulei JING Xinyi HAO | 2021 | Chinese Journal of Aeronautics2021，34，8： | 2 |
| 5 | 某燃气轮机涡轮动叶片腐蚀疲劳失效分析显示文摘针对某燃气轮机涡轮第1级动叶叶身表面涂层剥落及尾缘转接R处产生疲劳裂纹的现象进行了失效分析,并对失效机理进行探讨。首先,对失效叶片开展了理化检查,包括外观检查、化学成分分析及显微组织分析;然后模拟了机组运行时涡轮叶片的温度场和应力场分布。研究结果表明:重油中的S和V燃烧后产生硫酸盐和钒酸盐,局部高温促使其加速穿过陶瓷隔热层中的空隙并产生反应,从而使涂层出现脱落;温度场计算获得的局部高温区域与涂层剥落区域吻合;叶片应力模拟计算结果显示尾缘应力水平较高,频繁的启停使尾缘转接R处产生疲劳裂纹。基于研究结果,得出此次叶片失效的主要原因是腐蚀疲劳失效,并对涡轮叶片使用提出了合理的建议。 | 隋永枫 蓝吉兵 魏佳明 余沛坰 王建明 | 2022 | 热力发电2022，51，12： | 2 |
| 6 | Coupling damage and reliability model of low-cycle fatigue and high energy impact based on the local stress–strain approach显示文摘Fatigue induced products generally bear fatigue loads accompanied by impact processes,which reduces their reliable life rapidly. This paper introduces a reliability assessment model based on a local stress–strain approach considering both low-cycle fatigue and high energy impact loads.Two coupling relationships between fatigue and impact are given with effects of an impact process on fatigue damage and effects of fatigue damage on impact performance. The analysis of the former modifies the fatigue parameters and the Manson–Coffin equation for fatigue life based on material theories. On the other hand, the latter proposes the coupling variables and the difference of fracture toughness caused by accumulative fatigue damage. To form an overall reliability model including both fatigue failure and impact failure, a competing risk model is developed. A case study of an actuator cylinder is given to validate this method. | Chen Hongxia Chen Yunxia Yang Zhou | 2014 | Chinese Journal of Aeronautics2014，27，4： | 1 |
| 7 | An orientation-dependent creep life evaluation method for nickel-based single crystal superalloys显示文摘This paper aims to propose a creep life evaluation method considering the effect of crystallographic orientation.First,the maximum Schmid factor of{111}〈112〉and the corresponding lattice rotation angle were introduced to form an“orientation factor”.Then the equivalent stress was calculated by multiplying this factor and the nominal stress.Latterly,the Larson-Miller Parameter(LMP)method was adopted as the rupture life evaluation criteria,in which the input variable was the equivalent stress instead of the nominal stress.All the predictions showed high accuracy when the proposed method was applied to Mar-M247,SC7-14,CMSX-2,Alloy454,CMSX-4 and DD6.Finally,the applicable temperature ranges of the orientation-dependent method(using equivalent stress)and the traditional LMP method(using nominal stress)were discussed.The results show that only the Orientation-Dependent(OD)method is reliable at intermediate temperatures(760–850°C)because the orientation has significant effect on the stress rupture life,while the influence of orientation is considerably reduced at high temperatures.Both methods provide precise predictions in this situation,and the LMP method should be favored since it is much easier to implement. | Duoqi SHI Tianxiao SUI Zhenlei LI Xiaoguang YANG | 2022 | Chinese Journal of Aeronautics2022，35，1： | 0 |
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