一种微型涡轮发动机导向器改进方案  

Improvement of a micro-turbine nozzle

作　　者：宣建光[1] 邱建[1] 夏晨[1] 黄国平[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》2010年第12期2690-2696,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50576034);基础预研项目

摘　　要：为了提高发动机性能,克服微型涡轮发动机(MTE)的尺度小等因素导致其导向器内流动损失大的缺点,采用了整体叶片式导向器设计技术对某MTE-C微型发动机涡轮导向器进行了改型设计.首先采用NAPA软件对MTE-C微型发动机的整体叶片式导向器进行数值模拟,通过流场分析得到了原型导向器设计中导致流动效率低下的不足之处,并以此为理论依据,对导向器进行了改进.改进型导向器的整级数值模拟结果表明,涡轮在设计点的效率提高了15%,且在宽广的工作范围内其通流能力和效率均得到了明显的提升.The compact configuration and small size of the micro-turbine engine（MTE） cause the large flow loss in the micro-turbine nozzle,so the micro-turbine nozzle has been modified to reduce the flow loss and improve the performance.The numerical simulation of the original turbine nozzle was completed by NAPA program,and the reasons for the low performance were acquired by flow field analysis.The vaned turbine nozzle was improved and the performance comparison between original and improved turbine nozzles was completed.The efficiency of turbine stage at designing point increases by 15%,and the flow rate and efficiency of turbine stage are enhanced remarkably within a wide working range.

关 键 词：微型涡轮发动机 涡轮导向器 数值模拟 改进设计 流量特性 效率特性 

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]