空气涡轮起动机包容性数值仿真与结构优化设计方法研究

Numerical simulation and structure optimization design method of air turbine starter containment

运输类飞机适航条款明确规定空气涡轮起动机等含高能转子的设备必须具备足够的轮盘破裂包容能力,但国内相关单位普遍缺乏空气涡轮起动机包容结构的正向优化设计方法。为解决该问题,本文采用有限元数值仿真方法开发出多参数优化的自动化计算软件平台和流程,通过建立包容环结构的多参数实验设计(Design of Experiments,DOE)样本数据库,根据样本数的优化结果构建Kriging近似模型,并利用有限元计算获得最优的结构设计参数。该方法选取U形包容环截面的厚度δ,槽宽a,槽深h和槽缘宽s等参数进行优化,采用数值仿真和试验验证相结合的方式进行对比分析。结果表明,优化后的包容环径向变形量可达到29.7%,相比于优化前的18.9%具有明显提升;优化后的包容环径向变形更充分、吸能效果更好,在相同包容性条件下减重效果高达38%。通过采用本文提出的结构优化设计方法,实现了某型空气涡轮起动机包容环的正向优化设计,该方法可用于在役空气涡轮起动机包容环的优化与新型号空气涡轮起动机包容环设计。

The airworthiness regulations of transport aircraft clearly specify that the high-energy rotor equipment must have sufficient disk rupture containment capacity.However,the domestic manufacturer generally lack the forward optimization design method for the containment structure of air turbine starter.In order to solve this problem,an automatic calculation software platform and process for multi parameter optimization were developed by using the finite element numerical simulation.By establishing the multi-parameter Design of Experiments(DOE)sample database of the containment ring structure,the Kriging approximate model is constructed according to the optimization results of the samples,and the optimal structural design parameters are obtained by finite element calculation.In this method,the optimize parameters of the U-shaped containment ring include section thicknessδ,groove width a,groove depth h and groove side width s.Comparative analysis is carried out through simulation and test.The results show that the radial deformation of the optimized ring can reach 29.7%,which is significantly higher than that of the original 18.9%.The optimized containment ring has more sufficient radial deformation and better energy absorption effect,and the weight reduction effect is up to 38%under the same containment conditions.By adopting the structural optimization design method proposed in this paper,the forward optimization design of the containment ring of an air turbine starter is realized.This method can be used to optimize the containment ring of the air turbine starter in service or a new air turbine starter.