CAJ | 학술논문

利用自主开发的三维流场求解器 MFlow，基于混合平面法技术对航空发动机压气机流场进行了数值模拟。在转／静子交界面处的不同的展向位置，将流动周向平均后进行传递，使得非定常流动问题简化成为“准定常”问题，从而将计算过程简化为只需要对一个叶片流道进行计算，大大减小了计算量。通过计算得到了压气机的总体工作特性和几个关键气动参数的展向分布曲线，并将结果与试验数据进行了对比分析。计算结果和试验数据基本吻合，验证了计算程序的适用性和可靠性。
이용자주개발적삼유류장구해기 MFlow，기우혼합평면법기술대항공발동궤압기궤류장진행료수치모의。재전／정자교계면처적불동적전향위치，장류동주향평균후진행전체，사득비정상류동문제간화성위“준정상”문제，종이장계산과정간화위지수요대일개협편류도진행계산，대대감소료계산량。통과계산득도료압기궤적총체공작특성화궤개관건기동삼수적전향분포곡선，병장결과여시험수거진행료대비분석。계산결과화시험수거기본문합，험증료계산정서적괄용성화가고성。
An in-house three-dimensional unstructured-grid flow solver based on a mixing plane method was used to simulate the flow field of the compressors.Pitchwise averaging was used at the rotor/stator interface for information transport,making the unsteady problem to be-come a “qusi-steady”one.Thereafter the computational gird needs only one flow passage,which greatly reduced the amount of the calculation.Two different transonic compressors,NASA rotor 67 and stage 35,were tested in this paper.The overall performance maps and spanwise profiles of several aerodyamic parameters were obtained from the calculation,and the results were com-pared to the experiment data.The results presented here including pressure ratio,temperature ratio and adiabatic efficiency are in good agreement with the experiment data,indicating the ap-plicability and reliability of the method.