Axial Loss Development in Low Pressure Turbine Cascades
Axial Loss Development in Low Pressure Turbine Cascades
复制标题
低压涡轮叶栅的轴向损失发展
DOI：
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发表时间：
2012
期刊：
影响因子：
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通讯作者：
R. Niehuis
中科院分区：
文献类型：
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作者：
B. Muth;R. Niehuis
本文的目的是通过广泛的数值模拟来详细研究低压涡轮的性能。利用通用软件ANSYS CFX进行了数值模拟。特别关注叶栅流道内轴向损失的发展。结果表明，现代CFD工具能够将涡轮型线的整体损失分解为依赖于附加和分离流区的组成部分。此外，数值结果允许显示的组成损失取决于雷诺数。本文提出的轴向损失发展分析方法可以对数值结果的质量进行更全面的研究和评价。因此，本文还证明了该方法能够量化轴向速度密度比、来流湍流度、来流角和雷诺数对叶栅损失形态和流动角的影响，并对稳态和瞬态结果进行了比较。在喷气推进研究所的高速叶栅风洞中获得了lpt叶栅的验证数据。为此，实验在Re2th = 40000到400000的范围内进行。为了在真实的发动机运行条件下收集数据，风洞允许雷诺数和马赫数的独立变化。本文给出的实验结果包括详细的压力测量以及三维热线风速测量。然而，为了保护lpt设计的专有性，本文只显示了实验结果和数值结果的积分值。ASME版权所有©2012
The objective of this work presented in this paper is to study the performance of low pressure turbines in detail by extensive numerical simulations. The numerical flow simulations were conducted using the general purpose code ANSYS CFX. Particular attention is focused on the loss development in axial direction within the flow passage of the cascade. It is shown that modern CFD tools are able to break down the integral loss of the turbine profile into its components depending on attached and separated flow areas. In addition the numerical results allow to show the composition of the loss depending on the Reynolds number. The method of the analysis of axial loss development presented here allows for a much more comprehensive investigation and evaluation of the quality of the numerical results. For this reason the paper also demonstrates the capability of this method to quantify the influence of the axial velocity density ratio, the inflow turbulence level, the inflow angle and the Reynolds number on the loss configuration and the flow angle of the cascade as well as a comparison of steady state and transient results. The validation data of this LPT-Cascade have been obtained at the High Speed Cascade Wind Tunnel of the Institute of Jet Propulsion. For this purpose experiments were conducted within the range of Re2th = 40’000 to 400’000. To gather data at realistic engine operation conditions, the wind tunnel allows for an independent variation of Reynolds and Mach number. The experimental results presented herein contain detailed pressure measurements as well as measurements with 3-D-hot-wire anemometry. However, this paper shows only integral values of the experimental as well as the numerical results to protect the proprietary nature of the LPT-design.Copyright © 2012 by ASME