论文部分内容阅读
针对某高压燃气涡轮导叶前缘开设三排气膜孔冷气掺混进行了数值模拟,气膜孔流向夹角均为90°,径向射流角分别为30°,45°,60°和90°。采用网格预处理技术划分网格。详细分析了冷却流量占主流1.25%条件下,前缘冷气喷射对导叶型面气动参数和冷却效率的影响,对比研究了不同冷气流量与流动损失、涡轮级效率之间的关联。计算结果表明:冷气径向喷射角减小,冷却孔附近区域的静压、马赫数振动幅度也减弱。冷却流量增加,叶片表面的温度随之降低,但温度降幅逐渐减小。总压损失系数和能量损失系数随着冷气流量的增大而增加。导叶进口流量和涡轮级效率随着冷却流量的增加而减小。
A numerical simulation was carried out for the cold air blending with three rows of film holes opened on the leading edge of a high-pressure gas turbine guide vane. The included angles of film hole flow were 90 ° and the radial jet angles were 30 °, 45 °, 60 ° and 90 °, respectively °. Grid pretreatment grid technology. The influence of front air-cooling jet on aerodynamic parameters and cooling efficiency of guide vane is analyzed in detail when the cooling flow rate is 1.25% of the main flow rate. The correlation between different air flow rates and flow loss and turbine efficiency is compared. The calculation results show that the radial jet angle of cooling air decreases, and the static pressure and Mach number vibration amplitude in the vicinity of the cooling hole also decrease. As the cooling flow increases, the temperature of the blade surface decreases, but the temperature drop gradually decreases. The total pressure loss coefficient and energy loss coefficient increase with the increase of cold air flow. The guide vane inlet flow and turbine stage efficiency decrease as the cooling flow increases.