CAJ | 학술논문

本文通过数值模拟的方法研究了主流马赫数对圆柱孔、扇形孔及双射流气膜孔三种不同气膜孔结构冷却效果及气动损失的影响规律。结果表明，主流马赫数增加对圆柱孔和扇形孔的冷却效果影响不大；在较高吹风比条件下双射流气膜孔的冷却效果受主流马赫数的影响较大：在距离气膜孔较近位置气膜冷却效果随马赫数增大显著提高，更远位置气膜冷却效果显著下降。不同气膜孔结构的气动损失在吹风比较小时十分接近，随着吹风比的增大气动损失随之增大，相同吹风比条件下，气动损失随主流马赫数的增加而减小。
본문통과수치모의적방법연구료주류마혁수대원주공、선형공급쌍사류기막공삼충불동기막공결구냉각효과급기동손실적영향규률。결과표명，주류마혁수증가대원주공화선형공적냉각효과영향불대；재교고취풍비조건하쌍사류기막공적냉각효과수주류마혁수적영향교대：재거리기막공교근위치기막냉각효과수마혁수증대현저제고，경원위치기막냉각효과현저하강。불동기막공결구적기동손실재취풍비교소시십분접근，수착취풍비적증대기동손실수지증대，상동취풍비조건하，기동손실수주류마혁수적증가이감소。
Influence of different film cooling configurations on cooling effectiveness and aerodynamic losses of cylindrical hole, fan-shaped hole and double-jet hole has been studied by numerical simulation method.The results indicate that mainstream mach number has little impact on film cooling effectiveness of cylindrical hole and fan-shaped hole.Mach number has a great effect on film cooling ef-fectiveness of double-jet hole with a high blowing ratio:the film cooling effectiveness in the area near the film cooling hole improves sig-nificantly with the increase of mainstream mach number.On the contrary, the film cooling effectiveness in the area further downstream the film cooling hole drops with the increase of mainstream mach number.The aerodynamic losses of different film cooling configura-tions are approximate when blowing ratio is low, and losses would increase with the blowing ratio rising.When the blowing ratio re-mains the same, the aerodynamic losses would drop with the increase of mainstream mach number.