一种微型部分进气冲动式涡轮机设计方法  

A Design Approach of Micro Partial Admission Impusle Turbine

作　　者：蒋彬[1] 罗凯[1] 高爱军[2] 封启玺[2] 伊进宝[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705研究所,陕西西安710075

出　　处：《鱼雷技术》2015年第5期353-358,共6页Torpedo Technology

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

摘　　要：为弥补水下航行器微型部分进气冲动式涡轮机的设计缺陷,通过分析微型涡轮机的损失特性提出了一种微型水下涡轮机的设计方法,运用数值方法进行了方法合理性检验及变工况特性研究,并开展了实例设计。研究结果表明,所设计涡轮机的仿真内效率与设计值误差在3%以内;大背压下涡轮机叶栅和机匣能有效抑制喷管出口气流的分离;非设计转速下工质对叶栅的冲击损失会增大;通过调节喷管个数可满足较大范围内输出功率的需求。该方法可为微型部分进气冲动式涡轮机的优化设计和试验提供参考。For improving the current design method of micro partial admission impulse turbine, a design approach of the micro partial admission turbine is proposed by analyzing the micro turbine＇s loss characteristics. In addition, the rationality of the design approach is examined numerically, the variable working conditions are investigated, and the prototype is designed. The results indicate that the error of the designed turbine＇s inner efficiency between simulation results and the design parameters is less than 3%; the blade cascade and the shroud can suppress the flow separation at the nozzle＇s outlet under a big ambient pressure; the impact loss on the blade cascade increases under off-designed rotational speeds; the turbine can gain larger output power by changing nozzle number. The design method can provide a reference for the optimization design and test of the micro turbine.

关 键 词：微型冲动式涡轮机 部分进气 设计方法 变工况 内效率 

分 类 号：TJ630.32[兵器科学与技术—武器系统与运用工程]