微型冲动式部分进气涡轮机的流场特性及气动损失  

Flow Field Characteristics and Aerodynamic Losses of a Miniature Impulse Type Partial Admission Turbine

作　　者：蒋彬[1] 罗凯[1] 郑涛[2] 

机构地区：[1]西北工业大学航海学院,陕西西安710072 [2]中国船舶重工集团公司第703研究所,黑龙江哈尔滨150078

出　　处：《热能动力工程》2015年第6期873-879,969-970,共7页Journal of Engineering for Thermal Energy and Power

基　　金：国家自然科学基金资助项目(51409215);中央高校基本科研项目(G2015KY0102)

摘　　要：为研究微型冲动式部分进气涡轮机的流场及气动损失特性进而为水下航行器微型涡轮机设计提供参考,建立了2 k W级涡轮机的仿真模型并且通过与公开文献[2]实验结果进行对比验证了所建模型的可靠性,通过改变叶顶间隙、喷管出口与动叶间的轴向间隙、喷管扩张角、部分进气度的大小以及轮盘结构,研究了涡轮气动损失。结果表明:微型涡轮具有尺度效应,表现为喷管内声速点移至喉部下游,工作叶片表面的压力变化较为一致;随着上述几何参数的增大,涡轮内效率受叶顶间隙的影响最为明显,而轴向间隙的影响在一定范围内可以忽略,部分进气度为0.35时内效率上升趋于平稳,喷管扩张角为8°时的涡轮内效率高于6°和10°;无叶顶间隙时,除叶片之外的轮盘摩擦损失约为1%。To study the flow field and aerodynamic loss characteristics of a miniature impulse type partial admission turbine and then offer guidance for design of a miniature turbine for use in a underwater navigation vehicle,a simulation model for 2 k W class turbines was established and the reliability of the model was verified through a contrast with the results obtained from the literatures. Through changes in the blade tip clearance,axial clearance between the outlet of the nozzles and the rotating blades,divergence angle of the nozzles,partial admission degree and wheel disk structure,the aerodynamic loss of the turbine was studied. It has been found that the miniature turbine has a dimensional effect,which reflected by the fact that the acoustic velocity point in the nozzle shifts to the downstream of the throat of the nozzle and changes in the pressure on the surfaces of the working blades are relatively identical. With an increase of the geometrical parameters above-mentioned,the influence of the blade tip clearance on the inner efficiency of the turbine will be most conspicuous and the influence of the axial clearance,however,can be ignored.When the partial admission degree is 0. 35,the rise in the inner efficiency will tend to be stable and smooth. When the divergence angle of the nozzle is 8 degrees,the inner efficiency of the turbine is higher than that when the partial admission degree is 6 and 10 degrees respectively. When no blade tip clearance is present,the friction loss of the wheel disks not including the blades is about 1%.

关 键 词：微型冲动式涡轮机 部分进气 气动损失 数值模拟 内效率 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]