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针对高压涡轮叶尖主动间隙控制(ACC)机匣中的典型换热结构,利用试验研究了多层机匣结构中内斜向冲击射流的局部换热特征,重点分析了进口雷诺数(10 000~24 000)、冲击孔入射角度(30°,45°,60°)、冲击孔直径(1.0,1.5,2.0mm)等参数对带肋机匣表面局部和平均传热系数的影响规律.研究中发现加强肋的存在显著影响了机匣表面局部传热系数,同时由于冲击射流局部强化换热作用,多层机匣内表面不同位置的传热系数相差很大.试验结果表明:随着冷气进口雷诺数的增加,机匣加强肋表面局部和平均传热系数均提高.在研究参数范围内,冲击孔直径为2.0mm,孔数为23的情况下能够获得最佳的换热效果;相比30°和60°冲击孔入射角度,冲击孔入射角度为45°能获得更好的换热效果.
Aiming at the typical heat exchange structure in the high pressure turbine tip active clearance control (ACC) receiver, the local heat transfer characteristics of the internal oblique impinging jets in the multilayered receiver structure are experimentally studied. The inlet Reynolds number (10 000 ~ 24 000), impact angle (30 °, 45 °, 60 °) and diameter of impact hole (1.0, 1.5 and 2.0 mm) on the local and average heat transfer coefficient , It is found that the existence of stiffeners significantly affects the local heat transfer coefficient of the casing surface and the heat transfer coefficient differs greatly at different positions on the inner surface of the multi-layer receiver due to the locally intensified heat transfer of the impinging jets. The experimental results show that, With the increase of inlet Reynolds number, the local and average heat transfer coefficient increases on the surface of the stiffened rib of the casing, and the optimal heat transfer effect can be obtained under the condition of the diameter of 2.0mm and the number of holes of 23 in the study parameters. More than 30 ° and 60 ° impact hole angle of incidence, impact hole impact angle of 45 ° can get better heat transfer.