横流通道进气下等离子体改善气膜冷却特性

doi:10.16183/j.cnki.jsjtu.2024.296

摘要/Abstract

摘要：

采用数值模拟方法,基于建立的等离子体气动激励器模型,探究了横流通道进气条件下等离子体气动激励对气膜冷却特性的影响.分析了不同射流出流方式下等离子体激励气膜冷却流动特性,基于流场结构,揭示了横流进气时等离子体气动激励改善气膜冷却效果的作用机制,并获得了气膜冷却效率的变化规律.结果表明,横流通道进气腔冷却结构气膜孔出口附近存在4支涡结构,起源于孔内边界层流向旋度以及主流与射流剪切作用,涡尺寸、强度和演化过程受横流强度和吹风比的影响较大;施加等离子体激励后,在气膜孔出口附近形成了反肾形涡对,使得气膜对壁面的贴附效果增强,覆盖范围扩大,壁面气膜冷却效果均有所提高,但激励前后对孔流量系数影响不大;吹风比小于1.0时采用低雷诺数横流通道射流进气腔获得的冷却效率较高,吹风比大于1.0时高雷诺数横流通道射流进气腔的冷却效率较高.

关键词: 等离子体气动激励, 气膜冷却, 涡旋结构, 冷却效率, 横流

Abstract:

Using numerical simulation methods, this paper investigates the influence of a plasma aerodynamic actuator on the flow characteristics of film cooling under coolant crossflow conditions based on the established plasma aerodynamic actuator model. The flow field structures under different blowing ratios and inlet Reynolds numbers of the coolant crossflow channel are analyzed, and the mechanism by which the plasma actuator enhances film cooling performance is clarified. The variation of film cooling effectiveness is also obtained. The results show that four vortex structures form near the outlet of the film cooling hole, originating from the vorticity of the boundary layer inside the film cooling hole and the shear effect between the main flow and the jet flow. The size, strength, and evolution of these vortices are affected by the coolant crossflow Reynolds number and blowing ratio. After plasma excitation is applied, a new pair of vortices forms with a rotation direction opposite to that of the counter-rotating vortex pair. This enhances jet attachment to the wall and strengthens its spanwise spreading, thus improving film cooling effectiveness. The plasma aerodynamic actuator has little effect on the discharge coefficient. Under coolant crossflow conditions, film cooling effectiveness is higher at low Reynolds numbers when the blowing ratio is less than 1.0, whereas it is higher at high Reynolds numbers when the blowing ratio exceeds 1.0.

Key words: plasma aerodynamic actuation, film cooling, vortex structure, film cooling effectiveness, crossflow

中图分类号:

V231.1

张华磊, 赵子晨, 罗艳春, 吕雪燕. 横流通道进气下等离子体改善气膜冷却特性[J]. 上海交通大学学报, 2026, 60(8): 1352-1363.

ZHANG Hualei, ZHAO Zichen, LUO Yanchun, LÜ Xueyan. Plasma Actuator Enhancement of Film Cooling Performance Under Coolant Crossflow Conditions[J]. Journal of Shanghai Jiao Tong University, 2026, 60(8): 1352-1363.

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M	${\stackrel{-}{\eta }}_{\mathrm{a}\mathrm{r}\mathrm{e}\mathrm{a}}$,容腔进气,Re=3 200			${\stackrel{-}{\eta }}_{\mathrm{a}\mathrm{r}\mathrm{e}\mathrm{a}}$,横流进气,Re=3 750			${\stackrel{-}{\eta }}_{\mathrm{a}\mathrm{r}\mathrm{e}\mathrm{a}}$,横流进气,Re=15 000
M	无激励器	有激励器	提升比例/%	无激励器	有激励器	提升比例/%	无激励器	有激励器	提升比例/%
0.4	0.165	0.235	42.56	0.168	0.230	36.36	0.113	0.140	24.03
0.7	0.131	0.173	31.93	0.177	0.232	31.07	0.127	0.149	17.06
1.0	0.093	0.109	17.71	0.138	0.165	19.74	0.148	0.169	14.02
1.3	0.068	0.076	10.69	0.093	0.104	11.46	0.164	0.184	12.59

M	流量系数,容腔进气,Re=3 200			流量系数,横流进气,Re=3 750			流量系数,横流进气,Re=15 000
M	无激励器	有激励器	变化比例/%	无激励器	有激励器	变化比例/%	无激励器	有激励器	变化比例/%
0.4	0.595	0.591	-0.61	0.639	0.635	-0.62	0.600	0.603	0.42
1.0	0.657	0.656	-1.34	0.694	0.712	2.55	0.693	0.706	1.98