摘要
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。
This paper numerically simutates three rows holes of a high-pressure gas turbine stator on the leading edge. The injection angles of the row of holes are 30° ,45°, 60° and 90° to the radial direction, respectively, the lateral direction angles are all 90 deg. The pretreatment technology is used in dividing mesh grid. It also analyzes the influence of the leading edge of film cooling effect on the surface aerodynamic parameters and cooling efficiency on condition that the cooling mass flow is 1.25% of main flow and com- pares and studies the association between the different mass flow rate and flow losses, the efficiency of the turbine stage. The re- sults show that when the radial jet angle decreases, the vibration amplitude of pressure and mach number near the area of cooling hole is weakened, the temperature of the blade decreases with Cooling mass flow increases, but the amplitude of temperature grad- ually decreases. The total pressure loss coefficient and energy loss coefficient increases with the mass flow increase. The stator inlet flow and efficiency of turbine stage are decreased with the cooling mass flow increased.
出处
《机械制造与自动化》
2013年第5期10-15,共6页
Machine Building & Automation
关键词
冷气掺混
网格预处理
冷却效率
流动损失
涡轮级效率
coolant injection
pretreatment technology
cooling efficiency
flow losses
efficiency of turbine stage
