CAJ | 학술논문

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.
위료연구어뢰와륜궤통류도내적류동특정진이지도와륜통류결구설계,재합리간화모형기출상,채용계산류체역학(CFD)방법대순충동식어뢰와륜발동궤전자동협류도내초음속류동상황진행료수치방진,상세분석료협책내류동상황、총압손실、협편기동재하화온도재하.방진결과표명,동협류도내류동비교복잡,공각대기내적류동유교대영향,해수치월대,부면층분리월엄중,격파월강,총압손실야월대;동일개협편재경과분취류역시,기기동재하정현선증대후감소적추세,수교변적기동력작용,이협편기동승수재하월대기온도재하취월소,협편내적온도제도취월소.
To study fluid characteristic in torpedo turbine flow passages and guide structure design of the flow passag-es, 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.