航空发动机吞冰损伤一体化数值模拟平台搭建与验证  

Construction and Verification of An Integrated Platform for Numerical Simulation of Ice Ingestion Damage for Aeroengines

作　　者：沈安庆 徐惊雷[1] 夏全忠 夹福年 姚艳玲 SHEN An-qing;XU Jing-lei;XIA Quan-zhong;JIA Fu-nian;YAO Yan-ling(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AECC Sichuan Gas Turbine Establishment,Mianyang Sichuan 621010,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航发四川燃气涡轮研究院,四川绵阳621010

出　　处：《航空发动机》2023年第4期146-152,共7页Aeroengine

摘　　要：为了给航空发动机在进气条件下的吞冰损伤物理试验提供多方案快速优化的数值参考,建立了航空发动机叶片吞冰损伤快速分析的数值模拟方法和流程,并形成了1套软件系统。该系统通过研究发动机进气吞冰过程中冰体6自由度运动姿态和轨迹的流场快速模拟方法,建立了吞冰流场的数值仿真模型;通过冰体的本构模型及冰体撞击叶片损伤效应的系统研究,准确建立了叶片损伤模型;将吞冰流场计算和冰撞击过程计算进行了一体化耦合,形成了航空发动机叶片吞冰损伤的快速分析软件系统,建立了冰块运动姿态、冰块撞击叶片破碎过程及轨迹预测的一体化仿真流程。结果表明:数值计算方法能够有效预测冰块运动轨迹和撞击变形量,变形量误差不大于8%;该软件系统有效地解决了吞冰损伤复杂过程有限元模型的自动生成问题,极大地提高了分析效率,可有效节约试验成本、提高试验效率。A integrated numerical analysis system,which is capable of rapidly analyzing the effect of ice ingestion and the damage to aeroengine fan blades,was developed to provide multiple optimized numerical references for aeroengine ice ingestion tests.The flow field of ice ingestion was developed by the numerical simulation of both the 6-degrees-of-freedom(6 DOF)attitude and the trajectory of ice.The damage model of the impacted blades was generated accurately by the systematic study of the constitutive model of ice and the impact damage effect brought by the ice.The rapid analysis software system was established by integrating the calculation of the ice ingestion flow field and the ice impact process,which is capable of simulating the attitude of ice,the transient impact process,as well as the prediction of the trajectory of the fragmentized ice.The results show that the numerical calculation method can effectively predict the trajectory of ice and the amount of impact deformation,and the deformation error is less than 8%.The system can effectively solve the problem of the autogeneration of finite element model for the complex process of ice ingestion and damage,thus improving the analysis efficiency significantly,saving test cost,and improving test efficiency.

关 键 词：吞冰流场 叶片撞击损伤效应 一体化数值分析系统 航空发动机 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]