数据与计算发展前沿 ›› 2020, Vol. 2 ›› Issue (6): 11-20.

doi: 10.11871/jfdc.issn.2096-742X.2020.06.002

• 专题:高性能计算在行业领域的特色应用 • 上一篇    下一篇

显式动力学子模型法在航空发动机整机瞬态冲击并行计算中的应用

柴象海1,2,*(),胡寿丰1,2,张执南3,侯亮1,2   

  1. 1. 中国航发商用航空发动机有限责任公司, 上海 200241
    2. 中国航空研究院上海分院, 上海 200241
    3. 上海交通大学机械与动力工程学院, 上海 200240
  • 收稿日期:2020-09-03 出版日期:2020-12-20 发布日期:2020-12-29
  • 通讯作者: 柴象海
  • 作者简介:柴象海,中国航发商用航空发动机有限责任公司,博士,研究员级高级工程师,主要从事航空发动机瞬态冲击力学仿真分析与试验验证方法研究。本文中主要负责通过自编译子模型加载载荷算法的方式,实现了边界载荷从整机模型到分析对象的加载,载荷转换效率和转换精度自主可控,并通过试验设计对子模型数值仿真精度进行了验证。
    CHAI Xianghai, Ph.D., the professor and senior engineer of AECC Commercial Aircraft Engine Co., LTD, is mainly engaged in simulation analysis and experimental verification method of transient impact mechanics of aero-engine.In this paper, he is mainly responsible for the realization of boundary load loading from the whole machine model to the analysis object by the way of self-compiled sub model loading algorithm. As the result, the load conversion efficiency and conversion accuracy are controlled independently, and the accuracy of numerical simulation of the sub model is verified by experimental design.E-mail: chaixianghai@sohu.com|胡寿丰,中国航发商用航空发动机有限责任公司,博士,首席专家,主要从事航空发动机结构强度及复合材料结构件研发。本文中主要负责对子模型建模方法进行理论指导,提出载荷提取及加载策略。
    HU Shoufeng, Ph.D, the Chief expert of AECC Commercial Aircraft Engine Co., LTD, is mainly engaged in the research and development of structural strength of aeroengine and composite structural parts.In this paper, he is mainly responsible for the theoretical guidance of sub model modeling method, and puts forward the load extraction and loading strategy.E-mail:shoufenghu@163.com|张执南,上海交通大学,博士,副教授,主要从事碰磨载荷作用机理研究。本文中主要负责对航空发动机整机建模与仿真。
    ZHANG Zhinan, Ph.D., the associate professor of Shanghai Jiaotong University, is mainly engaged in the research on the mechanism of impact and wear loads.In this paper, he is mainly responsible for modeling and Simulation of aeroengine.E-mail: zhinanz@sjtu.edu.cn|侯亮,中国航发商用航空发动机有限责任公司,硕士,主管设计师,主要从事航空发动机整机仿真并行计算效率与一致性控制策略研究。本文中主要负责提供高效、高精度的航空发动机整机FBO高性能并行计算方法。HOU Liang, Master, the Chief designer of AECC Commercial Aircraft Engine Co., LTD, is mainly engaged in the research of parallel computing efficiency and consistency control strategy of aero-engine simulation.In this paper, he is mainly responsible for providing high-efficiency and high-precision parallel computing method for FBO of aero-engine.E-mail: houl66@163.com
  • 基金资助:
    上海科委项目(17DZ1120000)

Application of Explicit Dynamic Sub-Model Method in Parallel Calculation of Aero-Engine Transient Impact

CHAI Xianghai1,2,*(),HU Shoufeng1,2,ZHANG Zhinan3,HOU Liang1,2   

  1. 1. Department of Discipline Engineering, AECC Commercial Aircraft Engine Co., LTD, Shanghai 200241, China
    2. Shanghai branch of China Institute of Aeronautical Research, Shanghai 200241, China
    3. School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
  • Received:2020-09-03 Online:2020-12-20 Published:2020-12-29
  • Contact: CHAI Xianghai

摘要:

【背景】商用航空发动机需要满足适航安全性要求,其中风扇叶片脱落载荷是在设计中必须考虑的安全设计载荷。发动机整机瞬态显式动力学分析是个有效的分析工具,但在模型规模、计算效率和计算精度方面存在矛盾。整机模型通过选用合适的并行计算策略,一般能提供较为准确的部件界面载荷,但对于单个部件的应力分析,往往由于网格密度不够而不能获得满意结果。【方法】整机瞬态显式动力学仿真子模型技术,采用航空发动机整机简化模型进行整机计算,通过预先设置的子模型边界输出零部件载荷,作为零部件精细模型动强度分析的输入,在保证计算精度的同时,使计算效率大幅度提高。【结果】本文通过一个机匣等效平板靶板冲击试验算例,将平板特定区域定义为子模型,计算结果表明,子模型法能够与局部细化的整体模型得到相同的计算结果。同时,以航空发动机风扇轴为例,将子模型技术应用于叶片飞脱载荷下零部件动力学分析,建立航空发动机整机瞬态显式动力学仿真子模型分析方法,既可以解决叶片脱落等效载荷方法整机层面对粗网格部件应力分析计算误差大的问题,又能够考虑零部件细观结构对强度计算结果的影响。

关键词: 航空发动机, 整机包容性分析模型, 动力学仿真子模型, 并行计算

Abstract:

[Background] Commercial aero-engine needs to meet the requirements of airworthiness safety, in which the fan blade shedding load must be considered in the design. Transient explicit dynamic analysis of engine is an effective analysis tool, but there are some contradictions in model scale, calculation efficiency and calculation accuracy. Generally, the whole machine model can provide more accurate component interface load by selecting appropriate parallel computing strategy. However, for the stress analysis of single component, the grid density is not enough to obtain satisfactory results. [Methods] The sub-model technology for whole engine transient explicit dynamic simulation uses the simplified model of aero-engine to calculate the whole machine. The load of parts is output through the pre-set sub model boundary, which is used as the input of dynamic strength analysis of the fine model of parts. The calculation accuracy is guaranteed and the calculation efficiency is greatly improved. [Results] In this paper, a specific area of the plate is defined as a sub model through an example of an equivalent plate impact test of a casing. The calculation results show that the sub model method can obtain the same calculation results as the whole model with local refinement. At the same time, taking the aero-engine fan shaft as an example, the sub model technology is applied to the dynamic analysis of parts under the load of blade flying off, and the sub model analysis method of aero-engine transient explicit dynamic simulation is established, which can not only solve the problem of large calculation error of the blade shedding equivalent load method for coarse grid component stress analysis, but also consider the influence of the microstructure of the components to the results of strength calculation.

Key words: aero engine, whole engine FBO analysis model, dynamic sub-model technology, parallel computing