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为拓展某小型部分进气亚声速涡轮的应用能力,要求进一步提高其气动性能。使用Numeca商用计算流体力学软件建立了原型部分进气涡轮流道的全环域网格,进行了流场的粘性数值仿真,通过与相同叶型全周进气式涡轮的流场对比分析,揭示了部分进气式涡轮的流动机理和流动损失分布规律。在流场结构研究的基础上,对原型涡轮的动叶进行了改型优化,将动叶叶型由原来的纯冲击式叶型改为略带反力度的叶型,流场仿真结果表明涡轮效率提高了5个百分点。通过对改型前后2种部分进气式涡轮气动参数分布情况的对比分析,表明略带反力度的动叶叶型能有效减小部分进气式涡轮非进气扇区动叶通道内的回流损失,对提高涡轮性能有利,可为同类涡轮的气动设计提供参考。
In order to expand the application capability of a small part intake subsonic turbine, it is required to further improve its aerodynamic performance. The Numeca commercial computational fluid dynamics software is used to establish the full-area grid of the intake turbine section of the prototype and the viscous numerical simulation of the flow field is carried out. By comparing with the flow field of the same airfoil turbine of the same blade type, Part of the intake turbine flow mechanism and distribution of flow losses. Based on the study of the flow field structure, the rotor blades of the prototype turbine are modified and optimized, and the blade type of the turbine blade is changed from the purely impingement blade type to the blade type with slight counterforce. The simulation results of the flow field show that the turbine Efficiency increased by 5 percentage points. By comparing and analyzing the aerodynamic parameters distribution of two types of intake air turbine before and after modification, it is shown that the rotor blade with slight reaction force can effectively reduce the backflow in the non-intake fan flow passage of some intake turbines Loss, to improve the performance of the turbine is good, can provide reference for the aerodynamic design of similar turbines.