涡轮发动机喷嘴叶栅总损失的测定方法

A. Lapuzin, V. Subotovich, Y. Yudin, S. Naumenko
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引用次数: 0

摘要

为了评估蒸汽轮机和燃气轮机喷管叶栅气动效率的水平,提出了以总损失系数代替动能损失系数的方法,该方法同时考虑了动能损失和运动损失。这种方法使我们能够将叶栅后原来的非均匀空间流动转化为轴对称的圆柱形流动。在经向边界为圆柱形的环形叶栅中,总损失系数比动能损失系数约高0.02。在对涡轮机进行热计算时,考虑到运动损失,我们消除了对喷嘴叶栅的动能损失系数进行0.01-0.03的不合理修正的需要,从而提高了计算的准确性。为了分析喷嘴叶栅各个部分的运行情况,确定动能损失和运动损失之间的关系,建议使用2021年提出的平均方法,将叶栅后初始的非均匀空间流动转化为轴对称的锥形流动。这种流动的气动特性是广泛使用的动能损失因子和两个平均气流角。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
The Method of Determining Total Losses in the Nozzle Cascades of Turbomachines
To assess the level of aerodynamic efficiency of the nozzle cascades of steam and gas turbines, the method was suggested to determine the total loss coefficient instead of kinetic energy loss coefficient that takes into account both kinetic energy losses and kinematic losses. This method allows us to transform the original non-uniform spatial flow behind the cascade into an axisymmetric cylindrical flow. In the tested annular cascade with cylindrical meridional boundaries, the total loss coefficient is approximately 0.02 higher than the kinetic energy loss coefficient. By taking into account kinematic losses when performing thermal calculations for the turbines we eliminate the need for an unjustified correction of the kinetic energy loss coefficient of the nozzle cascade by 0.01–0.03, increasing thus the accuracy of calculations. To analyze the operation of individual sections of the nozzle cascade and to determine the relationship between kinetic energy losses and kinematic losses, it is advisable to use the averaging method proposed in 2021 that enables the transformation of the initial non-uniform spatial flow behind the cascade into an axisymmetric conical flow. The aerodynamic characteristics of this flow are the widely used kinetic energy loss factor and two averaged flow angles.
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