论文部分内容阅读
为深入掌握高压涡轮叶片带肋回转通道在旋转状态下的换热分布,建立了旋转内通道实验系统,利用瞬态液晶测量方法研究了动叶回转内通道模型的换热机理,比较了三维数值模拟和实验的换热结果。通道入口雷诺数为5000~17000,旋转数为0~0.09,旋转半径与水力直径之比为46.4。结果表明:不同雷诺数下回转内通道的局部换热系数分布相似,局部、平均换热系数均随雷诺数增加而增大;沿程展向平均换热系数呈多波峰状分布,肋的扰动强化换热沿流向逐渐减弱;径向出流通道的努赛尔数随旋转数增加明显增大,径向入流通道的努赛尔数随旋转数的增加略有减小;哥氏力使转弯下游通道的局部换热系数改变,肋间的高换热区域由前肋的背风面附近向两肋之间偏移。
In order to further understand the heat transfer distribution of the ribbed swirl channel in high-pressure turbine under rotating condition, a rotating inner channel experimental system was established. The transient heat transfer mechanism of the inner rotor channel model was studied by transient liquid crystal measurement. Simulation and experimental heat transfer results. The entrance Reynolds number is 5000 ~ 17000, the rotation number is 0 ~ 0.09, the ratio of rotation radius to hydraulic diameter is 46.4. The results show that the local heat transfer coefficients are similar in the rotary inner channels under different Reynolds numbers, and the local and average heat transfer coefficients increase with the increase of Reynolds number. The average heat transfer coefficient along the span exhibits multi-wave peak distribution and rib disturbance The intensified heat transfer decreases gradually along the flow direction. The Nusselt number of the radial outflow channel increases with the increase of the rotation number. The Nusselt number of the radial inflow channel slightly decreases with the increase of the rotation number. The local heat transfer coefficient of the downstream channel changes, and the high intercostal heat exchange area is offset from the vicinity of the leeward surface of the front rib to the two ribs.