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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >ISENTROPIC SWIRLING FLOW THROUGH SUPERSONIC NOZZLES - PART Ⅰ (FREE VORTEX FLOW)
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ISENTROPIC SWIRLING FLOW THROUGH SUPERSONIC NOZZLES - PART Ⅰ (FREE VORTEX FLOW)

机译：通过超音速喷嘴的等熵旋流-第一部分（免费涡流）

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摘要

An analytical model has been developed and an approximate solution for the free vortex swirling supersonic flow through nozzles. Earlier work by Mager, is potential flow based. In the present model swirl number has been redefined to confine the flow properties within the valid range. Flow properties are always determined by the total conditions (P_0 and a_0), nozzle profile and swirl intensity as in the case of one-dimensional flow. Integral form of the continuity equation has been used in order to satisfy the boundary conditions, since radial velocity component is ignored. For free vortex case, it has been shown that there exists a minimum radius along the length of the nozzle at which the density is zero and flow seems to be void causing reasonable blockage to the flow at throat. In defining the non-dimensional swirl number (β), axial velocity at each section was employed for non-dimensionalization as compared to Mager's definition of using a global constant to find swirl number (α). The variations of performance parameters of the nozzle such as co-efficient of discharge (C_d) thrust efficiency (η_s) and impulse efficiency (η_I) and flow field parameters such as density, pressure, velocity etc. are presented as a function of swirl numbers (α, β) and compared with the available experimental data. The swirl numbers (α, β) are also correlated.
机译：已经开发了一个解析模型，并为通过喷嘴的自由涡旋涡流超音速流动提供了近似解决方案。 Mager的早期工作是基于潜在流量。在本模型中，旋流数已被重新定义以将流动特性限制在有效范围内。流动特性始终由总条件（P_0和a_0），喷嘴轮廓和涡旋强度决定，就像在一维流动的情况下一样。由于忽略了径向速度分量，因此已使用连续性方程的积分形式来满足边界条件。对于自由涡流情况，已经显示出沿着喷嘴的长度存在最小半径，在该半径处密度为零并且流动似乎是空的，从而导致对喉咙处的流动的合理阻塞。在定义无量纲旋流数（β）时，与使用全局常数求得旋流数（α）的马格（Mager）的定义相比，采用了每个截面的轴向速度进行无量纲化。喷嘴性能参数的变化（如排放系数（C_d），推力效率（η_s）和脉冲效率（η_I））以及流场参数（如密度，压力，速度等）随旋流数而变化（α，β）并与可用的实验数据进行比较。旋流数（α，β）也相关。

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