某微型发动机轴流涡轮与向心涡轮的气动性能及尺寸对比分析  

Comparison research on performance and size of micro axial turbine and radial turbine

作　　者：夏晨[1] 黄国平[1] 邱建[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2011年第3期489-497,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(50576034);基础预研项目

摘　　要：为确定厘米级微型涡轮发动机在相对较大功率、流量需求时的涡轮形式,基于某直径为12cm的微型发动机样机开展研究.估算了该样机整机环境下单级轴流涡轮的做功能力,并按参数优选规律设计了一台微型轴流涡轮,将之与该样机采用的微型向心涡轮对比,分析了两种叶轮在功率、效率及尺寸质量方面的差别.研究表明:在先进微型发动机压比提高(>4)的情况下,涡轮为了保持效率且满足压气机更高功率需求,轴流式必须采用双级方案,向心式单级即可满足要求;在压气机压比为4～6条件下,进一步对比双级轴流与单级向心方案的结果显示,当流量小于500g/s时,向心式具有尺寸质量优势,发动机能实现较高的推质比.针对厘米级微型发动机,在发动机压比较高且没有超出单级向心涡轮做功能力的范围时,向心涡轮方案是更好的选择.The selection of an axial turbine or a radial turbine is a key problem for advanced micro-turbine engine with larger mass flow rate and power.A comparative research was completed to determine the suitable turbine form.For a micro-turbine engine of 12 centimeters diameter,one-dimension estimative model of axial turbine was established,and the output characteristic of axial turbine was analyzed.A micro axial turbine was designed,and the differences of power,efficiency,size and mass between the axial turbine and radial turbine were compared.The results indicate that：axial turbine has more compact size and lighter mass,but radial turbine has larger power.For an advanced micro-turbine engine,when the total pressure ratio of the compressor exceeds 4,a two-stage scheme is required for the axial turbine to provide enough power output,rather than one-stage for radial turbine.The comparison between two-stage axial turbine and one-stage radial turbine indicates that,radial turbine-stage has smaller size and mass when the flow rate is less than 500 g/s,and the total pressure ratio is 4～6,and the engine has a high thrust-mass ratio.So when a high pressure ratio is required but the power output of one-stage radial turbine isn＇t exceeded,the radial turbine has more advantages.

关 键 词：微型涡轮发动机 轴流涡轮 向心涡轮 压比 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]