摘要
为了研究鱼雷涡轮机通流道内的流动特征进而指导涡轮通流结构设计,在合理简化模型基础上,采用计算流体力学(CFD)方法对纯冲动式鱼雷涡轮发动机转子动叶流道内超音速流动状况进行了数值仿真,详细分析了叶栅内流动状况、总压损失、叶片气动载荷和温度载荷。仿真结果表明,动叶流道内流动比较复杂,攻角对其内的流动有较大影响,该数值越大,附面层分离越严重,激波越强,总压损失也越大;同一个叶片在经过喷嘴流域时,其气动载荷呈现先增大后减小的趋势,受交变的气动力作用,而叶片气动承受载荷越大其温度载荷就越小,叶片内的温度梯度就越小。
To study fluid characteristic in torpedo turbine flow passages and guide structure design of the flow pas- sages, the flow field in rotor blade cascade of an impulse supersonic torpedo turbine was numerically investigated by computational fluid dynamics （CFD） method. The detail information of flow, total pressure loss, and aerodynamic load and temperature load on a blade were analyzed. Simulation results show that： flow in rotor flow passages is very com- plicated; blade incidence angle exerts significant effect on the flow; the larger the incidence angle, the more severe the boundary layer separation, the stronger the shock wave, and the more the total pressure loss; when a blade is pass through the nozzle area, the aerodynamic load on it first increases and then decreases; heavier aerodynamic load leads to smaller temperature load and temperature gradient in the blade.
出处
《鱼雷技术》
2013年第1期43-47,共5页
Torpedo Technology
关键词
鱼雷涡轮机
动叶栅
流动特性
热传递
数值仿真
torpedo turbine
rotorblade cascade
flow characteristic
heat transfer
numerical simulation
