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采用三维非定常数值模拟计算某重型燃气轮机第一级透平的全气膜冷却特性,探讨级环境下静叶表面与静叶端壁及动叶表面与动叶平台的气膜非定常特性及泛冷却效应.燃气轮机泛冷却是指燃气轮机透平冷却气体出流在非设计位置所引起的附加效果.该部分工作包含两部分内容,第二部分关注级环境下动叶表面与动叶平台的气膜冷却特性,以及动静叶间隙轮缘密封出流在下游动叶栅中所形成的泛冷却效应.结果表明,在上游尾迹影响下,动叶中截面压力及动叶表面与平台的气膜冷却效率分布呈现较强的非定常性;动静叶间隙轮缘密封出流在平台上形成气膜覆盖,同时在动叶吸力面近尾缘叶根区域形成泛冷却效应,且形成泛冷却效应的范围相比静叶更大;此外,静叶全气膜能够进一步强化该区域的泛冷却效应.
The three-dimensional unsteady numerical simulation is used to calculate the gas film cooling characteristics of the first stage turbine of a heavy gas turbine. The gas film unsteady characteristics of the static and dynamic blade endwalls, Cooling effect Gas turbine pan cooling refers to the gas turbine turbine cooling gas flow in the non-design location caused by the additional effect.This part of the work contains two parts, the second part of the concern environment level moving blade surface and the moving blade platform gas film Cooling characteristics and the pan-cooling effect formed by the seal ring flow at the clearance between the stator and rotor were analyzed.The results show that under the influence of the upstream wake, the cross-section pressure in the moving blades and the film cooling efficiency The distribution of the dynamic and static vanes seals the outflow on the platform to form a gas film covering, and at the same time, a pan-cooling effect is formed on the near-trailing edge root region of the moving blade suction surface and a pan-cooling effect is formed In addition, the static leaf gas film can further strengthen the pan-cooling effect in this area.