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结合现有燃气轮机气膜冷却成果,提出一种气膜加热防冰理论。基于控制容积法,针对NACA63(2)-215翼型,采用Realizable k-ε紊流模型,桨叶气膜孔出射角90°,对风力机桨叶三维流场进行详细的数值模拟。分析了气膜加热的基本原理,总结了不同攻角下翼型前缘、升力面和压力面气膜的流动特性、传热特性和加热有效度。研究表明:叉排布置气膜覆盖效果相对好于顺排布置;攻角是影响气膜的流动和传热特性重要因素之一;翼型壁面换热峰值位于气膜孔附近,并随着攻角的变化,吸力面和压力面的流动特性呈非单调性变化;当攻角为5°时,3个射流近孔区域都能形成较好的热气覆盖效果,吸力面与压力面的气膜加热有效度基本相同,加热效果相对较好。模拟结果与实验研究进行对比,两者变化趋势基本一致。
Combined with the existing gas turbine cooling results, a gas film heating anti-icing theory is proposed. Based on the control volume method, a Realizable k-ε turbulence model is adopted for the NACA63 (2) -215 airfoils. The 3D numerical simulation of the three-dimensional flow field of the airfoil is carried out with a 90 ° exit angle of the airfoil. The basic principle of gas film heating was analyzed. The flow characteristics, heat transfer characteristics and heating efficiency of air film at different angles of attack were summarized. The results show that the air film covering effect of fork row arrangement is relatively better than that of the film arrangement. The angle of attack is one of the important factors affecting the flow and heat transfer characteristics of the air film. The peak heat transfer of airfoil wall is located near the film hole, The change of angle, the change of non-monotonicity of the suction surface and the pressure surface showed a good monotonicity. When the angle of attack was 5 °, Heating effectiveness is basically the same, the heating effect is relatively good. The simulation results are compared with the experimental study, the trend of the two is basically the same.