Full-Annulus Simulations of Airfoil Clocking in a 1-1/2 Stage Axial Compressor
Full-Annulus Simulations of Airfoil Clocking in a 1-1/2 Stage Axial Compressor
复制标题
1-1/2 级轴流式压缩机中翼型时钟的全环空模拟
DOI：
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发表时间：
1999
期刊：
影响因子：
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通讯作者：
N. Savin
中科院分区：
文献类型：
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作者：
D. Dorney,;D. Sondak;P. Cizmas;V. Saren;N. Savin
轴流压气机由于动、静叶型之间的相对运动而具有固有的非定常流场。这种相对运动导致叶片排之间的粘性和非粘性（潜在）相互作用。随着翼型中级数的增加，对流尾流的形成会导致尾流/尾流和尾流/翼型相互作用逐渐变得更加复杂。定子或转子的相对周向位置的变化可以改变这些相互作用，导致翼型上不同的非定常强迫函数和不同的压气机效率。此外，随着马赫数的增加，由于潜在的影响，叶栅之间的相互作用会增强。实验和计算都表明，在交替叶栅中具有相同叶片数的多级轴向涡轮机中，翼型同步可以用来提高效率和减少不稳定性。虽然以前的调查提供了一个更好的理解与翼型时钟的物理，需要更多的研究，以确定是否翼型时钟是可行的，用于现代燃气轮机压缩机。本文介绍了一个结合实验/计算研究工作的结果，研究高速轴流压气机中的翼型时钟的物理。本文对一个1-1/2级高速压气机的静叶型在八种不同的时序位置进行了数值模拟。为了精确地模拟实验压气机，使用34个IGV、35个转子和34个定子翼型进行了全环模拟。通常的做法是修改叶片数，以减少进行气动模拟所需的计算工作，并且迄今为止进行的所有计算时钟研究都采用了这种近似方法。在本研究中，还使用1个进口导叶、1个转子翼型和1个定子翼型进行了模拟，以模拟每个具有34个翼型的叶片排，以检查这种近似的效果。检查了时间平均和非定常数据（包括性能和边界层数量）。预测结果表明，模拟整个环隙与实验数据有更好的定性一致性，并且可以更准确地模拟相邻叶片排之间的相互作用。Copyright © 1999 by ASME
Axial compressors have inherently unsteady flow fields because of relative motion between rotor and stator airfoils. This relative motion leads to viscous and inviscid (potential) interactions between blade rows. As the number of stages increases in a turbomachine, the buildup of convected wakes can lead to progressively more complex wake/wake and wake/airfoil interactions. Variations in the relative circumferential positions of stators or rotors can change these interactions, leading to different unsteady forcing functions on airfoils and different compressor efficiencies. In addition, as the Mach number increases the interaction between blade rows can be intensified due to potential effects.It has been shown, both experimentally and computationally, that airfoil clocking can be used to improve the efficiency and reduce the unsteadiness in multiple-stage axial turbomachines with equal blade counts in alternate blade rows. While previous investigations have provided an improved understanding of the physics associated with airfoil clocking, more research is needed to determine if airfoil clocking is viable for use in modern gas-turbine compressors. This paper presents the results of a combined experimental/computational research effort to study the physics of airfoil clocking in a high-speed axial compressor. Computational simulations have been performed for eight different clocking positions of the stator airfoils in a 1-1/2 stage high-speed compressor. To accurately model the experimental compressor, full-annulus simulations were conducted using 34 IGV, 35 rotor and 34 stator airfoils. It is common practice to modify blade counts to reduce the computational work required to perform turbomachinery simulations, and this approximation has been made in all computational clocking studies performed to date. A simulation was also performed in the present study with 1 inlet guide vane, 1 rotor airfoil, and 1 stator airfoil to model blade rows with 34 airfoils each in order to examine the effects of this approximation. Time-averaged and unsteady data (including performance and boundary layer quantities) were examined. The predicted results indicate that simulating the full annulus gives better qualitative agreement with the experimental data, as well as more accurately modeling the interaction between adjacent blade rows.Copyright © 1999 by ASME