CAJ | 학술논문

采用 SST k-ω紊流模型模拟旋转状态下4种曲率半径(R/D ＝30,R/D ＝75,R/D ＝120和R/D ＝∞)叶片的气膜冷却效果.分析讨论吹风比分别为0．5和1．5,旋转数分别为0．03768,0．07536及0．11304时,曲率和旋转数对叶片吸力面和压力面气膜冷却特性的影响.结果表明：旋转数一定时,曲率半径越小叶片的吸力面和压力面气膜轨迹偏转越明显；当曲率半径变大时,吸力面高 Nu 区域面积增大,叶片表面传热效果增强；压力面高 Nu 区域面积减小,叶片压力面气膜冷却效果减弱；旋转数的增大使得小曲率半径叶片吸力面表面传热减弱,大曲率半径叶片的压力面表面传热降低.
채용 SST k-ω문류모형모의선전상태하4충곡솔반경(R/D ＝30,R/D ＝75,R/D ＝120화R/D ＝∞)협편적기막냉각효과.분석토론취풍비분별위0．5화1．5,선전수분별위0．03768,0．07536급0．11304시,곡솔화선전수대협편흡력면화압력면기막냉각특성적영향.결과표명：선전수일정시,곡솔반경월소협편적흡력면화압력면기막궤적편전월명현；당곡솔반경변대시,흡력면고 Nu 구역면적증대,협편표면전열효과증강；압력면고 Nu 구역면적감소,협편압력면기막냉각효과감약；선전수적증대사득소곡솔반경협편흡력면표면전열감약,대곡솔반경협편적압력면표면전열강저.
The turbulence model was employed to simulate film cooling effect of blade with four radius of curvatures in rotating state.The effects of curvature and rotating number on film cooling performance of the convex surfaces and concave surfaces was investigated,under conditions with blowing ratio of 0.5 and 1.5,and the rotating number of 0.037 68,0.075 36 and 0.1 13 04.The results show that,with a constant rotating number,the lower the radius of curvature,the more obvious the gas film deflection of the convex surfaces and concave surfaces.Increasing the radius of curvature will enlarge the area of convex surface with high Nu number and enhance the heat transfer,while the concave surfaces had the opposite results.In addition,increasing the rotating number will weaken the heat transfer on convex surfaces with low radius of curvature and that on concave surfaces with high radius of curvature.