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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。
In order to improve the comprehensive performance of micro-turbojet, the single-stage radial turbine guide is improved. In the improved design, the physical laryngeal area of the guide and the full three-dimensional aerodynamic means are used to optimize the blade profile to improve the aerodynamic performance of the turbine stage. The numerical calculation shows that at the near design point, the turbine flow increases by about 12.5% and the efficiency increases by about 2.5%. Engine performance tests show that: at design speed, the thrust increase of 21.7%, 12% lower fuel consumption. Improved design of the performance of the turbine guide to meet the overall requirements of the engine.