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跨音压气机转子叶尖间隙复杂流动观测 总被引:8,自引:1,他引:7
本文利用高频响动态压力传感器,在文献[1]的基础上,对WP11压气机转子叶尖间隙 流场进行了流场测量。测试包括三个转速多个节流条件下的间隙流场。测试结果表明:激波总体位 置随节流加深而向上游移动,但吸力面最小压力点基本维持在40%或20%弦长处不变。当激波位 置在该点之后时,二次漏流直接冲击激波结构;当激波位置在该点之前时,激波结构基本只受前缘 漏流的影响。 相似文献
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应用遗传算法求解二维扩压器壁面速度最优分布 总被引:3,自引:0,他引:3
将遗传算法应用于求解透平机械中的二维扩压器壁面最优化速度分布,该方法可以容易的求解出既满足在扩压器出口流动速度极小又保证壁面边界层不发生分离的最优速度分布。用该方法求取著名的Stratford实验条件下的二维扩压器最优速度分布,所得结果与该实验吻合良好。 相似文献
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A compressible three-dimensional design method for radial and mixed flow turbomachinery blades 总被引:1,自引:0,他引:1
M. Zangeneh 《国际流体数值方法杂志》1991,13(5):599-624
A fully three-dimensional compressible inverse design method for the design of radial and mixed flow turbomachines is described. In this method the distribution of the circumferentially averaged swirl velocity rV θ on the meridional geometry of the impeller is prescribed and the corresponding blade shape is computed iteratively. Two approaches are presented for solving the compressible flow problem. In the approximate approach the pitchwise variation in density is neglected and as a result the algorithm is simple and efficient. In the exact approach the velocities and density are computed throughout the three-dimensional flow field by employing a fast fourier transform in the tangential direction. The results of the approximate and exact approach are compared for the case of a high-speed (subsonic) radial-inflow turbine and it is shown that the difference between the blade shapes computed by the two methods is well within the manufacturing tolerances. The method was validated by calculating the flow through a designed high-speed radial-inflow turbine by using a three-dimensional inviscid Euler solver. Very good correlation was obtained between the specified and computed rV θ-distributions. 相似文献
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Effects of free stream turbulence on the distribution of heat transfer around turbine blade sections
Local convective heat transfer coefficients to a number of modern gas turbine blade sections have been measured under a wide range of mainstream conditions, from notionally steady flows to highly perturbed turbulent flows. The paper discusses the results and, through a detailed analysis of the pertinent boundary layer flow parameters and their relation to the observed experimental results, tests criteria for the occurrence of transition from laminar to turbulent boundary layers, a factor which all the data from this work confirm as critical in predicting the quantitative effects of mainstream turbulence on heat transfer rates. Artificially induced mainstream turbulence, which is endemic in the flows in a real turbine, enhances significantly the heat transfer rates, especially to the leading edge regions and on the pressure surface, particularly when the acceleration is tending to suppress transition. The results presented here confirm existing criteria for laminarisation and the applicability of some of those available for predicting laminar-turbulent transition. The observations also demonstrate how surface geometry can influence the stability of the flows, and the uncertainties which remain in assessing the effect of Goertler vortices and their role in the convective heat transfer process. 相似文献
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A new method based on the anisotropic tensor force finite element and Taylor-Galerkin finite element is presented in the present
paper. Its application to two-dimensional viscous transonic flow in turbomachinery improves the convergence rate and stability
of calculation, and the results obtained agree well with the experimental measurements. 相似文献
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叶轮机设计的缘线匹配理论及方法 总被引:1,自引:0,他引:1
本文提出了叶轮机非定常设计的缘线匹配理论和方法,研究指出,缘线匹配注意了先前没有被考虑的周期非定常流动的相位影响,而今通过协调相邻叶排相邻缘线空间关系得以实现。初步理论及数值研究表明缘线匹配技术在提高叶轮机气动性能、气弹性能、气动噪声和热传导性能上的潜力。作为一个设计自由度,它使叶轮机非定常气动设计具有了真实而可操作的内容。 相似文献
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F. Bassi L. Botti A. Crivellini N. Franchina A. Ghidoni 《International Journal of Computational Fluid Dynamics》2016,30(4):307-328
In this work the capabilities of a high-order Discontinuous Galerkin (DG) method applied to the computation of turbomachinery flows are investigated. The Reynolds averaged Navier–Stokes equations coupled with the two equations k-ω turbulence model are solved to predict the flow features, either in a fixed or rotating reference frame, to simulate the fluid flow around bodies that operate under an imposed steady rotation. To ensure, by design, the positivity of all thermodynamic variables at a discrete level, a set of primitive variables based on pressure and temperature logarithms is used. The flow fields through the MTU T106A low-pressure turbine cascade and the NASA Rotor 37 axial compressor have been computed up to fourth-order of accuracy and compared to the experimental and numerical data available in the literature. 相似文献