高速涡轮发动机压缩部件低雷诺数影响研究

Research on the Influence of Low Reynolds Number on the Compression Component of High-speed Turbine Engine

为了分析马赫数3.0量级高速涡轮发动机在高空22.5 km范围内,雷诺数变化对多级压气机气动性能的影响,采用Was⁃sell特性修正与经验曲线拟合的方法,评估了低雷诺数条件压气机工作点效率、压比、流量的变化。利用S1计算程序分析了低雷诺数条件下基元叶型的流动特征,探讨了减小雷诺数影响的叶型设计规律。通过加入转捩模型的3维仿真模拟了地面和高空典型工况的气动特性,分析了低雷诺数对多级压气机稳定性的影响。结果表明:压气机在高空18.5 km和22.5 km喘振裕度相比地面条件下分别减小了5.61%和8.12%。综合对比仿真法和经验法对多级压气机性能预测结果,认为仿真法考虑了多效压气机在低雷诺数条件下级间匹配变化的影响,更适用于对压气机高空全转速特性的预测。

In order to analyze the influence of Reynolds number variation on the aerodynamic performance of a multi-stage compressor at altitude range of 22.5 km for Mach number 3.0 high-speed turbine engine,the Wassell characteristic correction and empirical curve fitting were used to evaluate the changes of efficiency,pressure ratio,and flow rate at the compressor operating point at low Reynolds number.By using a program of S1,the flow characteristics of the airfoil under the condition of low Reynolds number were analyzed,and the design law of the airfoil to reduce the influence of Reynolds number was discussed.The aerodynamic characteristics of typical ground and altitude conditions were simulated by three-dimensional simulation with transition model,and the influence of low Reynolds number on the stability of the multi-stage compressor was analyzed.The results show that the surge margin of the compressor at 18.5 km and 22.5 km above the ground are reduced by 5.61%and 8.12%respectively.By comprehensively comparing the performance prediction results of the multi-stage compressor by simulation method and empirical method,it is considered that the simulation method takes into account the influence of multi-stage the compressor on the matching variation between stages at low Reynolds number conditions,and is more suitable for the prediction of compressor's high-altitude full-speed characteristics.