CAJ | 학술논문

采用数值研究方法并结合实验数据系统地研究了马赫数对离心压缩机小流量系数基本级性能的影响,对基本级内的流动损失机理及马赫数对静止部件性能进行分析.研究结果表明由于小流量系数基本级具有较窄的轴向通道宽度,边界层堵塞效应在小流量系数基本级损失机理中起到关键作用.在马赫数比较小时随马赫数的增加级性能显著提高,达到一定的马赫数后基本级性能又随着马赫数增加而下降.无叶扩压器和回流器的性能受各自进口绝对马赫数的影响很小,静止部件的性能主要受各个部件的进口气流角以及相对宽度的影响.
채용수치연구방법병결합실험수거계통지연구료마혁수대리심압축궤소류량계수기본급성능적영향,대기본급내적류동손실궤리급마혁수대정지부건성능진행분석.연구결과표명유우소류량계수기본급구유교착적축향통도관도,변계층도새효응재소류량계수기본급손실궤리중기도관건작용.재마혁수비교소시수마혁수적증가급성능현저제고,체도일정적마혁수후기본급성능우수착마혁수증가이하강.무협확압기화회류기적성능수각자진구절대마혁수적영향흔소,정지부건적성능주요수각개부건적진구기류각이급상대관도적영향.
Narrow flow channel typically generate considerable efficienly losses in centrifugal compressor stages.The performances of two centrifugal compressor model stages with low flow coefficients are studied by performing three dimensional numerical simulation and experimental investigations.The loss mechanisms in these stages and the effects of Mach number on stage performance are analysed using the numerical simulation results.The results show that the boundary layer blockage effect plays a key role in the compressor stage for extremely narrow channel width at low flow coefficients.Unlike what is generally accepted that the performance of stage decreases with increaseing Mach number,the centrifugal stage at low Mach number,shows a higher performance for increasing Mach number.Only after reaching a certain Mach number,the performance of stage decreases with increasing Mach number.The performance of vaneless diffuser and return channel of the stage at low coefficient is almost independent of the Mach number,and the performance of these stationary components is governed by the inlet flow angle and their relative width.