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本文介绍了叶片式扩压器离心压气机特性曲线的计算。计算表明:1.叶片和壳罩之间的间隙损失计算是很理想的,其间隙可看作收缩系数为1的薄膜缝隙。2.通过对无叶扩压器进口到叶片扩压器喉口间的二维边界层计算,可很好地确定扩压器喉口的阻塞。3.借助于叶片进口气流方向与叶片吸力面之间夹角的修正,利用简化扩压器的试验结果来计算叶片扩压器的静压恢复是可行的。本文还介绍了两个不同压气机的特性曲线计算及与实测结果的比较。结果表明,除喘振线外,其吻合度是令人满意的。 根据叶片扩压器入口段边界层的分离原理所确定的理论喘振线与其中一台压气机的实测喘振线是一致的。
This article describes the calculation of the characteristic curve of the centrifugal compressor of a vane diffuser. The calculation shows that: 1. The calculation of the gap loss between the blade and the shell is very good, and the gap can be regarded as the film gap with the contraction coefficient of 1. 2. By calculating the two-dimensional boundary layer between the leafless diffuser inlet and the vane diffuser throat, the blockage of the diffuser throat can be well determined. 3. With the help of the correction of the included angle between the direction of the blade inlet airflow and the blade suction surface, it is feasible to calculate the static pressure recovery of the blade diffuser by using the simplified diffuser test results. This paper also introduced the calculation of the characteristic curves of two different compressors and the comparison with the measured results. The results show that, in addition to the surge line, its goodness of fit is satisfactory. The theoretical surge line determined according to the separation principle of the boundary layer of the inlet section of the vane diffuser is consistent with the actual surge line of one of the compressors.