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为了有效减少当前航空发动机轴流涡轮导向器的叶片排数,对多级无导叶对转涡轮的气动设计方法展开了研究.给出了该类型涡轮的基本结构和命名方法,介绍了使用该涡轮的发动机热力循环模拟和性能计算流程,提出了能够改善动叶进口预旋、提高级载荷和效率的设计方法。完成了一个由4排锥形动叶构成的高负荷多级无导叶对转涡轮气动设计,设计点总压比和总效率的数值模拟结果分别为10.4和91.2%,验证了设计方法的有效性.
In order to effectively reduce the number of blade rows of the axial-flow turbine guide of the aero-engine, the aerodynamic design method of multi-stage vaneless turbomachine is studied. The basic structure and nomenclature method of this type of turbine is given. Turbine engine thermodynamic cycle simulation and performance calculation process, proposed to improve the pre-rotating impeller imports, to improve the class load and efficiency of the design method. The aerodynamic design of a high-load multi-stage vaneless counter-rotating turbomachine with four rows of tapered blades is completed. The numerical results of total pressure ratio and total efficiency of the design point are 10.4 and 91.2% respectively, which proves the effectiveness of the design method Sex.