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首页> 外文会议>International Conference on Fracture and Damage Mechanics(FDM 2007); 20070717-19; Madeira(PT) >Fatigue Analysis of Forged Aerospace Components based on Micro Structural Parameters
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Fatigue Analysis of Forged Aerospace Components based on Micro Structural Parameters

机译：基于微观结构参数的锻造航空航天零件疲劳分析

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With the objective of creating a simulation model for the lifetime calculation of forged aerospace components it is necessary to clarify the damage mechanisms in the materials used. This has been researched for the Ni-base alloy Inconel 718 by varying the forging parameter effective plastic strain rate, which is realised by using three types of equipment: hydraulic press, screw press and hammer. Specimens processed at the screw press show the highest lifetime by keeping all other forging parameters unvaried. Micro structural investigations show that the amount and morphology of dominant as-large-as grains play a important role. This methodology is currently investigated for Ti-6A1-4V. Lifetime tests show that besides effective strain and anisotropy the influence of morphology is important. As soon as the model status allows lifetime analyses the thermo-mechanical process (forging and heat treatment) can be developed depending on the desired lifetime specifications in order to realise an interdisciplinary lifetime optimisation of forgings. A further aim is the use of basic coherences of safe-life and fail-safe approaches in the low and high cycle fatigue region in order to reasonable handle with flaws and defects at the edge layer.
机译：为了创建用于锻造航空航天部件寿命计算的仿真模型，有必要弄清所用材料的损坏机理。已经通过改变锻造参数有效塑性应变率对镍基合金Inconel 718进行了研究，这是通过使用三种类型的设备实现的：液压机，螺旋压力机和锤子。通过使所有其他锻造参数保持不变，在螺杆压力机上加工的试样具有最高的使用寿命。微观结构研究表明，主要晶粒的数量和形态起着重要作用。目前正在研究Ti-6A1-4V的这种方法。寿命测试表明，除了有效应变和各向异性外，形态学的影响也很重要。一旦模型状态允许进行寿命分析，就可以根据所需的寿命规格开发热机械过程（锻造和热处理），以实现锻件的跨学科寿命优化。另一个目的是在低和高循环疲劳区域中使用安全寿命和故障保险方法的基本一致性，以便合理处理边缘层的缺陷。

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