冷却剂参数对铣槽喷管低周疲劳寿命的影响

采用有限体积流固耦合计算方法、非线性有限元热结构耦合分析方法和局部应变法研究大面积比铣槽喷管三维再生冷却槽道在循环工作条件下的热结构变形与低周疲劳寿命,并对比分析了冷却剂质量流量与入口温度对铣槽喷管疲劳使用寿命的影响.计算结果表明,铣槽喷管热结构响应呈现复杂的三维效应,应变较大位置主要分布在与肋连接的内衬区域,喷管中部的残余应变量最大;冷却槽道低周疲劳寿命分布和热结构响应基本一致,最小寿命位于喷管中部与肋相连的内衬区域燃气侧;随冷却剂质量流量增加,铣槽喷管低周疲劳寿命不断提高;随冷却剂入口温度增加喷管尾部低周疲劳寿命值不断降低,而喷管中前部的低周疲劳寿命值却不断提高,当冷却剂入口温度为280K左右时,本文的铣槽喷管总体使用寿命达到最大.     

航天用铝合金/ 焊丝焊接性研究

针对2A14、2219、2195、2A97、1460铝合金,通过焊接热模拟试验、焊接裂纹敏感性试验和拉伸试验,建立了材料脆性温度区间大小和焊接性的关系及焊丝主成分和焊接性的关系。结果表明,试验合金焊接性从好到差的排列顺序为2219、2A14、1460、2195、2A97。其中2A14、2219铝合金现用焊丝可以满足推进剂贮箱用铝合金焊接性要求。脆性温度区间较小时,焊接性良好,随脆性温度区间增加,焊接性变差;采用满足主成分含量之和为6%的焊丝焊接时,若抗裂性满足要求,则接头延伸率满足要求。     

喷丸对DZ4 合金旋转弯曲疲劳断裂特征的影响

对喷丸前后DZ4高温合金旋转弯曲高周疲劳断口的断裂特征进行了观察.结果表明,室温和高温(820℃)时,未喷丸的DZ4合金高周疲劳裂纹均萌生于试样表面以及与表面相连的铸造缺陷或碳化物处.Kt=1时,疲劳断口为点源,源区存在滑移平面和滑移台阶;随着应力集中水平的升高(Kt=2,Kt=3),疲劳断口向多源和线源发展,源区滑移面变小甚至消失;随着温度的升高,断口源区滑移特征明显.喷丸后,疲劳裂纹源内移,裂纹萌生于试样次表面的晶体内部或铸造缺陷处.带缺口试样裂纹源减少,起源区域缩小,出现明显的主、次疲劳源.实验证明,喷丸可降低DZ4合金表面和缺口敏感性,对裂纹萌生有抑制作用,可提高材料的疲劳性能,随着温度升高,喷丸的强化作用逐渐减弱,但在820℃仍有强化作用.     

航空发动机涡轮部件断裂分析

某航空发动机使用中出现多级涡轮叶片和放气活门随动杆断裂故障,通过现场勘查、断口分析、金相检查和机理分析等手段,确定各断裂件的断裂模式,最终确认放气活门随动杆疲劳断裂是导致涡轮部件超温断裂的主要原因。并在此基础上,对相关工作提出建议。     

机身某部位连接区疲劳和损伤容限分析

从疲劳和损伤容限的概念出发,对某机身13长桁的框腹板进行受力情况、疲劳寿命、裂纹扩展寿命和剩余强度分析,充分讨论了与框腹板相连的接头的可靠性。在考虑精度的情况下用子模型的方式节省了很多计算时间,用扩展有限元法预测裂纹扩展的轨迹也与实验相吻合,为工程应用提供了简洁有效的途径。     

Effect of stress ratio on HCF and VHCF properties at temperatures of 20 °C and 700 °C for nickel-based wrought superalloy GH3617M

This paper attempts to investigate the effects of stress ratio and high temperature on the HCF(high-cycle-fatigue) and VHCF(very-high-cycle-fatigue) behaviors of nickel-based wrought superalloy GH3617 M. Fatigue tests over the full HCF and VHCF regimes were conducted on superalloy GH3617 M subjected to constant-amplitude loading at five stress ratios of -1, -0.5, 0,0.4, and 0.8 in environments of 20 °C and 700 °C temperatures. From experimental observation and fractographic analysis, fatigue mechanisms were deduced to reveal the synergistic interaction between high temperature and stress ratio on the HCF and VHCF behaviors of superalloy GH3617 M. A phenomenological model was crafted from available fatigue design knowledge to evaluate the synergistic interaction, and a good correlation between predictions and experiments has been achieved.     

Uncertainty propagation for statistical impact prediction of space debris

Predictions of the impact time and location of space debris in a decaying trajectory are highly influenced by uncertainties. The traditional Monte Carlo (MC) method can be used to perform accurate statistical impact predictions, but requires a large computational effort. A method is investigated that directly propagates a Probability Density Function (PDF) in time, which has the potential to obtain more accurate results with less computational effort. The decaying trajectory of Delta-K rocket stages was used to test the methods using a six degrees-of-freedom state model. The PDF of the state of the body was propagated in time to obtain impact-time distributions. This Direct PDF Propagation (DPP) method results in a multi-dimensional scattered dataset of the PDF of the state, which is highly challenging to process. No accurate results could be obtained, because of the structure of the DPP data and the high dimensionality. Therefore, the DPP method is less suitable for practical uncontrolled entry problems and the traditional MC method remains superior. Additionally, the MC method was used with two improved uncertainty models to obtain impact-time distributions, which were validated using observations of true impacts. For one of the two uncertainty models, statistically more valid impact-time distributions were obtained than in previous research.     

A model-based prognostics method for fatigue crack growth in fuselage panels

This paper proposes a model-based prognostics method that couples the Extended Kalman Filter (EKF) and a new developed linearization method. The proposed prognostics method is developed in the context of fatigue crack propagation in fuselage panels where the model parameters are unknown and the crack propagation is affected by different types of uncertainties. The coupled method is composed of two steps. The first step employs EKF to estimate the unknown model parameters and the current damage state. In the second step, the proposed efficient linearization method is applied to compute analytically the statistical distribution of the damage evolution path in some future time. A numerical case study is implemented to evaluate the performance of the proposed method. The results show that the coupled EKF-linearization method provides satisfactory results: the EKF algorithm well identifies the model parameters, and the linearization method gives comparable prediction results to Monte Carlo (MC) method while leading to very significant computational cost saving. The proposed prognostics method for fatigue crack growth can be used for developing predictive maintenance strategy for an aircraft fleet, in which case, the computational cost saving is significantly meaningful.     

冷挤压强化对GH4169合金孔结构室温低循环疲劳寿命影响

对GH4169合金中心孔板材试样进行冷挤压强化,测试了挤压前后GH4169中心孔板材试样在663 MPa/20℃条件下的低循环疲劳寿命;分别采用扫描电镜、X射线衍射残余应力仪、表面轮廓仪分析了疲劳断口、疲劳过程中残余应力场的演化以及表面形貌。结果表明:冷挤压强化后孔结构的疲劳寿命提高为原始试样的2.6倍。冷挤压强化对孔壁的强化效果使得冷挤压试样疲劳源萌生于倒角处单源,而原始试样萌生于孔壁多源。经过50000周次疲劳实验,冷挤压强化残余压应力有所松弛,但进口端与出口端的表面残余应力分别保持了55%和75%。冷挤压后孔壁表面粗糙度R_a由0.354μm减小到0.297μm。