Roman Maiboroda
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摘要

现代航空发动机的设计离不开数值模拟方法。在创建发动机的第一阶段,数值模拟的优势是显而易见的:能够在相当短的时间内探索不同的几何模型,而计算精度达到5…15%。数值实验的一个组成部分是进行测试问题,因此有必要确定必要的计算网格拓扑结构和湍流粘度模型。本研究针对基于STFF转子的超声速压气机叶栅流动仿真试验问题,选择计算网格拓扑结构和湍流黏度模型关闭Navier-Stokes方程组。在这项工作中,研究了四种计算网格和四种湍流粘度模型。日志含义自动修改时间步长。随时间变化的最大时间为0.00005…0.001 s。控制点设置在光栅的前面和后面,马赫数的值显示在那里。计算时,通过改变输入处的速度值来选择光栅前的马赫数。当叶栅输入输出马赫数达到,残差达到恒定值,且在后续迭代中不发生变化时,计算终止。构建了4种不同类型的结构化计算网格。选择3号网格进行进一步的计算,因为它与测试结果有足够的相似性,而且它的尺寸更小,可以加快计算速度。其次,对不同类型的湍流模型进行了计算。考虑了湍流模型SST、SST GTT、k-ω和RNG k-ε。对于所有湍流模型,边界层高度都是基于条件Y+ < 1来选择的。对计算结果的分析表明,采用SST - GTT湍流模式计算得到的误差最小。本文将叶栅截面的密度分布与现场实验所得的纹影照片进行了比较。对所得结果的定性分析表明,基于stff的压气机炉排周围的流动模式具有相似的性质,尤其是叶间通道和叶栅后面的边缘尾迹。因此,为了进一步研究风机内部的流动,我们选择了Mesh3计算网格的拓扑结构和紊流粘度模型SST GTT。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Моделювання течії в надзвуковій компресорній решітці
The design of modern aircraft engines cannot be imagined without numerical simulation methods. The advantages of numerical simulation at the first stages of creating engines are obvious: the ability to explore different geometric models in a fairly short time, while the accuracy of calculations reaches 5 ... 15%. An integral part of the numerical experiment is conducting test problems, because of which it is necessary to identify the necessary topology of the computational grid and the turbulent viscosity model. The current study conducts a test problem of flow simulation in a supersonic compressor cascade-based on the STFF rotor to select the topology of the computational grid and the turbulent viscosity model for closing the system of Navier-Stokes equations. In this work, four variants of the computational grid and four models of turbulent viscosity were studied. The time step was automatically changed. The maximum time over time was 0.00005…0.001 s. Control points were set in front of the grating and behind it, where the value of the Mach number was displayed. When calculating, the value of the Mach number in front of the grating was selected by changing the value of the velocity at the input. The calculation was terminated when the values of the Mach numbers at the input and output of the cascade were reached, as well as constant values of the residuals, which did not change during subsequent iterations. 4 variants of the structured type computational grid were built. Grid No. 3 was chosen for further calculations since it provides sufficient similarity with the test results, and it also has a smaller size, which makes it possible to speed up the calculation. Next, calculations are performed for different types of turbulence models. The turbulence models SST, SST GTT, k-ω and RNG k-ε were considered. For all turbulence models, the boundary layer height was chosen based on the condition Y+ < 1. An analysis of the calculation results showed that the smallest error was obtained in calculations with the SST GTT turbulence model. This paper presents a comparison of the density distribution in the cross-section of the cascade with a schlieren photograph obtained from a field experiment. A qualitative analysis of the obtained results shows that the flow patterns around the STFF-based compressor grate are of a similar nature, in particular, in the interblade channel and edge wakes behind the cascade. Thus, for further research to study the flow in the fan, the topology of the Mesh3 computational grid and the turbulent viscosity model SST GTT were chosen.
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