Abstract: In order to improve the performance of a micro-turbine engine， a single radial inflow turbine guide vane was redesigned with engine experiment and three-dimension aerodynamic method. The test was used to define vane throat， and the 3D method optimizes its blade profile to improve turbine aerodynamic performance.Numerical results show that the mass flow and efficiency increased by 12.5%， 2.5% at near design point， respectively. The experiment data of the engine indicated that the thrust of the engine increased by 21.7% and specific fuel consumption decreased by 12%. The optimized radial inflow turbine guide vane aerodynamic performance meet the engine general performance requirement.

Key words: Micro-turbine engine；Radial inflow turbine guide vane；Optimization

摘要： 为了提高微型涡喷发动机综合性能，对其单级向心涡轮导向器进行改进设计。改进设计中，采用发动机性能试验摸底导向器物理喉部面积，全三维气动手段优化叶片型线方法，提高涡轮级气动性能。数值计算得出:在近设计点处，涡轮级流量增加约12.5%，效率提升约2.5%。发动机性能试验表明:在设计转速下，推力增幅达21.7%，燃油耗油率降低12%。改进设计的涡轮导向器性能满足发动机总体要求。

关键词: 微型涡喷发动机；向心涡轮导向器；改进