雷诺数对跨音速压气机转子性能的影响

Effect of Reynolds Number on Transonic Compressor Rotor Performance

为了研究雷诺数对跨音速压气机转子性能的影响,基于NUMECA流场仿真软件对NASA设计压缩机进口级转子37进行气动研究。对比分析了不同进气压力下,Rotor37总体气动性能和内部流动细节。不同入口压力对应不同雷诺数。结果表明,在满足几何不变,压比不变,转速不变,入口总温不变的条件下,雷诺数进入自模化区后,基本可以忽视雷诺数对压气机转子气动性能的影响。在不考虑叶片粗糙度的情况下,雷诺数为设计雷诺数47倍时,绝热效率-流量特性曲线总体效率升高,最大绝热效率升高1.4%;压比-流量特性曲线向压比更高,折合流量更大偏移,最大压比几乎不变;当压力升高雷诺数升高后,压气机转子稳定运行区间宽度基本不变。

In order to study the influence of Reynolds number on the performance of transonic compressor rotor,the aerodynamic performance of NASA designed compressor inlet stage rotor 37 was studied based on NUMECA flow field simulation software.The aerodynamic performance and internal flow details of rotor37 under different inlet pressures were compared and analyzed.Different inlet pressure corresponds to different Reynolds number.The results show that under the conditions of geometric similarity,constant pressure ratio,constant speed and constant inlet temperature,the influence of Reynolds number on the aerodynamic performance of compressor rotor can be ignored when Reynolds number enters the self modeling region.When the Reynolds number is 47 times of the design Reynolds number,the overall efficiency of the adiabatic efficiency flow characteristic curve increases,and the maximum adiabatic efficiency increases by 1.4%;The pressure ratio flow characteristic curve deviates from the pressure ratio and the equivalent flow more,and the maximum pressure ratio is almost constant;When the pressure increases and the Reynolds number increases,the width of the stable operation region of the compressor rotor is basically unchanged.