CAJ | 학술논문

应用Standard k-ε紊流模型并结合SIMPLE算法，近壁区流动的处理采用壁面函数法，对燃气轮机首级静叶产生的非定常尾迹及动叶流场进行数值模拟。通过在动叶前放置直径为 d=2、4、6 mm 的圆柱来模拟静叶尾迹的宽度，研究不同时刻尾迹宽度对下游动叶传热特性的影响。结果表明：静叶产生的尾迹对下游动叶压力面与吸力面的速度影响呈现周期性变化，圆柱尾迹产生的速度亏损，使主流的流速降低，压力面低速回流区在1/4T 时刻达到最大。低吹风比M=0.5时，尾迹宽度增大(d=4 mm)能使压力面传热增强，而吸力面的传热变化很小，但过高的尾迹宽度(d=6 mm)将会同时降低压力面和吸力面的努赛尔数。高吹风比 M=1.5时，随着尾迹宽度增大，压力面和吸力面的传热均增强，在d=6 mm时努赛尔数达到最大。
응용Standard k-ε문류모형병결합SIMPLE산법，근벽구류동적처리채용벽면함수법，대연기륜궤수급정협산생적비정상미적급동협류장진행수치모의。통과재동협전방치직경위 d=2、4、6 mm 적원주래모의정협미적적관도，연구불동시각미적관도대하유동협전열특성적영향。결과표명：정협산생적미적대하유동협압력면여흡력면적속도영향정현주기성변화，원주미적산생적속도우손，사주류적류속강저，압력면저속회류구재1/4T 시각체도최대。저취풍비M=0.5시，미적관도증대(d=4 mm)능사압력면전열증강，이흡력면적전열변화흔소，단과고적미적관도(d=6 mm)장회동시강저압력면화흡력면적노새이수。고취풍비 M=1.5시，수착미적관도증대，압력면화흡력면적전열균증강，재d=6 mm시노새이수체도최대。
Using the standard k-ε turbulence model, SIMPLE algorithm and the wall function treatment, numerical simulation was performed to investigate in unsteady wake caused by turbine first static blade and rotor blade flow field. To change the width of wake by altering column diameter d=2, 4, 6 mm placed in front of rotor blade to study the influence of wake on the heat transfer characteristic of rotor blade at different moment. The results show that the unsteady wake caused by static blade affects the velocity of pressure side and suction side of rotor blade periodically. Velocity loss leads main stream velocity to decrease; low velocity recirculation zone comes to maximum at 1/4T. When blowing ratio M=0.5, wake width increases to d=4 mm will enhance heat transfer of pressure side, suction side changes slightly, while overlarge wake width d=6 mm will decrease the Nusselt number of pressure and suction side. When blowing ratio M=1.5, the Nusselt number of pressure and suction side will both increase with wake width increasing and comes to the maximum at d=6 mm.