摘要
设计了一种空气工质低压比的微小流量、高转速离心压缩机三元叶轮,并对其流场特性进行数值模拟.研究表明:该类叶轮出口与进口区域面积比小于1;采用高转速可以改善该类叶轮的效率;叶轮的最佳叶片数较源于大流量低转速离心压缩机理论的叶片数经验公式计算值要小;叶轮出口角一般在60°以上;叶尖顶部间隙增大时,叶轮总压比及效率显著下降.研究方法和结果为飞机高性能空气循环制冷系统和蒸汽压缩制冷系统中微小流量高转速离心压缩机的工程化设计提供了有益的参考.
A 3-D impeller for a micro flowrate high speed centrifugal air compressor （MHCAC） was designed and the performance of flow field was numerically studied. The results show that the ratio of outlet to inlet area of MHCAC impellers is less than 1.0, the efficiency of a micro flowrate centrifugal compressor can be improved by high rotating speed; the optimum number of blades of MHCAC impellers is less than that given by empirical formula originated from the theory of high flowrate-low speed centrifugal compressor; the out- let angle of a MHCAC impeller is generally bigger than 60°; the overall pressure ratio and ef ficieney of the impeller decrease with the increase of tip clearance. The methods and results of this paper provide valuable reference for engineering design of a MHCAC in aircraft air-cycle or vapor compression refrigeration systems.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第10期1896-1902,共7页
Journal of Aerospace Power
基金
航空科学基金(02E51039)
关键词
微小流量
高转速
离心压缩机
叶轮
性能
micro flowrate
high-speed
centrifugal compressor
impellersperformance
