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针对高压涡轮叶尖间隙主动控制机匣的多层结构,重点分析了机匣内部加强肋和安装螺栓共同组成的基本换热单元,利用热膜法研究了加强肋表面的局部和平均传热系数,得到了不同进气状态、加强肋高度对传热系数的影响规律。研究发现:冲击靶面传热系数随着冲击雷诺数的增长而增大,但传热系数的增长速率随着冲击雷诺数的增大而缓慢降低。3排冲击射流工况中,靠近出流位置的加强肋表面平均传热系数最高。试验结果表明,加强肋表面的传热系数受到加强肋高度和冲击雷诺数耦合作用。在高雷诺数时,增加加强肋高度带来的换热强化效果更加明显。
Aiming at the multi-layer structure of the active control casing of high-pressure turbine tip clearance, the basic heat exchange unit consisting of the stiffener inside the casing and the mounting bolt is analyzed emphatically. The local and average heat transfer coefficient The influence of different inlet conditions and height of ribs on the heat transfer coefficient was obtained. The results show that the heat transfer coefficient increases with the Reynolds number, but the heat transfer coefficient increases slowly with the Reynolds number. In the three-row impinging jet, the average heat transfer coefficient of the reinforcing rib near the outflow location is the highest. The experimental results show that the heat transfer coefficient of the rib surface is affected by the coupling between the rib height and the impact Reynolds number. At high Reynolds numbers, the effect of heat transfer enhancement due to increased rib height is more pronounced.