摘要
采用三维雷诺平均N-S方程求解方法,对某燃气轮机压气机进口级流动进行模拟,研究了峰值效率点及近失速点的性能及流动特性,探索叶片通道中引起高损失的原因,分析了静叶通道内复杂的流动结构及吸力面角区分离的产生机制。结果表明:当该压气机级向近失速工况推进时,静叶中的能量损失较导叶、动叶增长更快;静叶下端壁大范围低速流体是损失的主要来源;通道涡及泄漏涡是静叶通道内主要二次流,其共同作用造成大面积总压损失;近失速工况下沿流向和展向的逆压梯度增大且二次流增强,导致静叶吸力面下端壁角区分离现象的出现。
Three-dimensional steady Reynolds Averaged N-S simulations were conducted on a gas turbine inlet compressor stage of a gas turbine. Compressor performance and flow characteristics were analyzed at peak efficiency and near stall conditions to discover the reasons for high loss in blade passage. The complicated flow structures and forming mechanism of corner separation at suction surface in stator passage were clarified. Results indicated that energy loss in stator passage grew at the highest rate among three blade rows,as the compressor stage was marching on near stall condition. Low speed flow at the suction surface corner region was the major source of high loss. The main secondary flow phenomena inside the stator passage,passage vortex and leakage vortex,jointly contributed to massive total pressure loss. The appearance of corner separation at stator pressure surface endwall is caused by the increased adverse pressure gradient along streamwise and spanwise as well as the strengthened secondary flow at the near stall condition.
出处
《燃气轮机技术》
2016年第1期30-35,共6页
Gas Turbine Technology
基金
国家自然科学基金项目(51405384)
华能集团科技项目(HNKJ12-H22)
关键词
压气机
损失
二次流
角区分离
compressor
loss
secondary flow
corner separation
