航空发动机轮盘简化裂纹体建模

Simplified Cracked Body Modeling for Aeroengine Disk

中文关键词:  轮盘  损伤容限设计  简化裂纹体模型  临界裂纹尺寸  裂纹扩展寿命  航空发动机

英文关键词:aeroengine disk  damage tolerance design  simplified cracked body model  critical crack size  crack propagation life  aeroengine

中文摘要:

      为了满足航空发动机轮盘损伤容限设计评估方法发展的需求，开展了轮盘简化裂纹体建模方法研究。对轮盘盘心、辐 板、螺栓孔等关键部位可能存在的表面裂纹、内部裂纹等典型裂纹类型，根据轮盘的几何特征和载荷条件，利用商业软件对轮盘及 简化裂纹体模型进行裂纹扩展计算和对比分析，提出了基于轮盘不同部位特征和对应临界裂纹尺寸的简化裂纹体模型建立及选 取原则。结果表明：采用规则的简化裂纹体模型代替轮盘构件进行裂纹扩展分析，所计算的应力强度因子和裂纹尺寸随循环数的 变化曲线与实际轮盘计算结果均非常接近，临界裂纹尺寸计算差别在±10%以内，裂纹扩展寿命的计算差别在±5%以内。简化裂 纹体模型相较于实际轮盘的裂纹扩展寿命计算结果略偏保守。

英文摘要:

      In response to the growing need for the development of assessment methods for damage tolerance design in aeroengine disks, a study on simplified modeling methods for disk cracks was conducted. This research focused on typical crack types that could exist in key regions of the disk, such as the bore, web, and bolt holes. By utilizing the geometric characteristics of the disk along with its loading conditions, fracture mechanics analysis was performed on both the complete disk and simplified cracked body models using the commercial software. A comparative analysis was carried out to establish principles for selecting and constructing simplified cracked body models based on the characteristic features of different disk regions and their corresponding critical crack sizes. The results show that employing simplified cracked body models to replace the actual disk components for crack propagation analysis yields stress intensity factors and crack size variation curves with cyclic loading that closely resemble the computed results from the actual disk model. The calculated criti? cal crack size exhibited discrepancies within ±10%, and the predicted crack propagation life exhibited differences within ±5% compared to the actual disk calculations. The simplified cracked body models slightly err on the conservative side in estimating the crack propagation life, as compared to the actual disk's behavior.