论文部分内容阅读
针对某航空发动机涡轮导向器,采用数值模拟的方法研究了缘板安装缝隙泄漏流对叶栅通道流场结构及叶栅性能参数的影响,对比分析了不同泄漏流压力、缝隙宽度及缝隙相对位置条件下的泄漏量,及其对叶栅性能参数的影响规律.研究发现:在压差作用下冷气通过缘板安装缝隙进入燃气主流通道并在中段的位置形成螺旋涡系,对端壁二次流产生明显影响,其作用效果沿叶高方向逐渐降低,最大影响区域为44.44%叶高.计算结果表明:随着泄漏流压力的提高、缝隙宽度的增加、缝隙与发动机主轴方向夹角的变大,叶栅的能量损失系数和泄漏量都呈现出了单调增加的趋势.在研究的参数范围内,涡轮缘板安装缝隙导致的泄漏流可使叶栅的能量损失系数增加14%~62%.
Aiming at the turbine guide of an aeroengine, the influence of the leakage flow on the flow field of blade cascade and the performance parameters of cascades was studied by numerical simulation method. The influences of different leakage pressure, gap width and relative position of gap Under the conditions of leakage and its influence on performance parameters of the cascade.Research found that: under the pressure difference through the edge of the installation of cold air through the plate into the mainstream gas passage and in the middle of the formation of spiral vortex system, the end wall of the second The effect is greatly reduced along the leaf height direction, and the maximum impact area is 44.44% of the leaf height.The calculated results show that with the increase of leakage pressure, the increase of the slit width and the change of the angle between the slit and the main axis of the engine The energy loss coefficient and the leakage rate of large and cascades all showed a monotonous increasing tendency.The leakage loss caused by the installation of the turbine edge plate could increase the energy loss coefficient of cascades by 14% -62% within the parameter range studied, .