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提出一种基于S形曲线压气机过渡段造型方法.该方法将过渡段造型归结为S形内壁曲线拐点相对位置,面积分布率极值及其极值点相对位置3个几何控制因素.并采用此方法构造了一系列压气机过渡段,并针对这些过渡段进行三维数值模拟.结果表明:面积分布率极值是影响过渡段性能最重要的因素;可以通过调整面积分布率极值来控制过渡段最大面积处相对马赫数,减小外壁气流附面层厚度及支板形成的低压尾迹区;同时,配合变化较陡的内壁造型和合理的面积分布率曲线极值点相对位置,可以改善外壁形状,抑制附面层变厚.对于所研究的过渡段,内壁拐点相对位置为0.18,面积分布率极值点相对位置为0.20,相对马赫数为0.65时,总压损失最小.
A transition curve modeling method based on S-curve compressor is proposed, which is characterized by three geometrical controlling factors, namely the relative position of inflexion point, the extreme value of area distribution and the relative position of the extreme point of S curve, A series of compressor transition sections were constructed and the three-dimensional numerical simulation of these transition sections was carried out. The results show that the extreme value of area distribution ratio is the most important factor affecting the performance of transition section; the transition can be controlled by adjusting the extreme value of area distribution ratio The relative Mach number at the maximum area of the section reduces the thickness of the outer wall airflow laminar layer and the low-pressure wake area formed by the support plate. At the same time, in conjunction with the relatively steep wall shape and the relative position of the extremum point of the reasonable area distribution ratio curve, Shape and inhibit the thickening of the overburden.For the transitional section studied, the relative position of the inflexion point of the inner wall is 0.18, the relative position of the extreme point of the area distribution ratio is 0.20, and the relative pressure loss is the smallest when the relative Mach number is 0.65.