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本文论证了流面理论未能计及由举力场的扰动所诱导的二次流的影响,并以流面为基础,推导了轴流式涡轮机械中此类二次流场所遵循的一般方程式。流场的可压缩性用当地的基本流场M数来校正,避开了通常的线性化理论中用叶排上游M数或某个平均M数所带来的误差。基本流场的旋度影响用基本流场5_2中心流面的流片厚度b来代表。b=1代表了基本流场无旋或旋度影响可忽略的情形,b=0的极限情况代表了基本流场的旋度为无穷大的情况。从而为探索解决大剪切大扰动流场中的二次流问题提供了一种可能的途径。文中分析了一般方程在不可压平面叶栅流动和可压缩轴对称轴向进气流动中所具有的形式,并指出,在举力线理论的假设前提下,它们和文献[10—12]中的基本方程的形式相同,从而证明了本方程的适用性。
This paper demonstrates that the theory of flow surface fails to account for the influence of the secondary flow induced by the perturbation of the lifting field. Based on the flow surface, the general equation followed by such secondary flow field in axial turbomachinery . The compressibility of the flow field is corrected by the local elementary flow field M, which avoids the error caused by the M number of upstream leaves or some average M number in the general linearization theory. The curl effect of the basic flow field is represented by the thickness b of the flow sheet at the center flow surface of the basic flow field 5_2. b = 1 represents the case where the basic flow field is non-rotating or the curl effect is negligible. The limit case with b = 0 represents the case where the curl of the basic flow field is infinite. Thus providing a possible way to explore the secondary flow problem in large shear perturbation flow field. In this paper, we analyze the general equation in the form of incompressible plane cascade flow and compressible axisymmetric axial inlet flow, and point out that under the assumption of lifting line theory, they are similar to those in [10-12] The basic equations of the same form, which proves the applicability of this equation.