离心压气机无叶扩压段流路控制扩稳机理  

Stall improvement mechanism of vaneless diffuser flow path control in a centrifugal compressor

作　　者：王永生[1,2] 童志庭[1] 林峰[1] 聂超群[1] 

机构地区：[1]中国科学院工程热物理研究所先进能源动力重点实验室,北京100190 [2]中国科学院研究生院,北京100190

出　　处：《航空动力学报》2012年第9期2106-2112,共7页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2007CB210104);国家自然科学基金(51010007)

摘　　要：为寻求叶轮-扩压器间无叶扩压段流路控制的扩稳机理,选取某离心压气机为研究对象,利用数值模拟的方法,通过流场分析解释其失速机理,并在此基础上重新设计无叶扩压段机匣结构,探讨一种有效流路控制扩稳方式.分析结果表明:将无叶扩压段机匣结构设计为先收缩后扩张型后,离心压气机稳定工作范围提高了2.8%,但绝热效率有所降低.To investigate the stall improvement mechanism of vaneless diffuser flow path control,a centrifugal compressor was simulated and compared with existing experimental data.According to characteristics of flow field and stall mechanism,a convergent-divergent type of impeller-diffuser casing designed was analyzed.The result shows that the stable flow range of centrifugal compressor increases by 2.8%,however,no obvious positive effects are found on the adiabatic efficiency which is slightly lower than that of the prototype.

关 键 词：无叶扩压段 机匣结构 流路控制 扩稳 离心压气机 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]