近零冲角下大折转角正弯叶栅壁面静压的实验研究  

Experimental Investigation on Surface Static Pressure of Positive Curved Blade with Large Camber Angle at Near Zero Incidences

作　　者：陈绍文[1] 佟勇 

机构地区：[1]哈尔滨工业大学能源科学与技术学院,黑龙江哈尔滨150001 [2]总参陆航处驻哈尔滨地区军事代表室,黑龙江哈尔滨150066

出　　处：《燃气涡轮试验与研究》2006年第4期1-5,共5页Gas Turbine Experiment and Research

摘　　要：实验研究了近零冲角条件下叶片正弯曲对某大折转角扇形扩压叶栅壁面静压的影响。结果表明:直叶片吸力面静压系数等值线呈现明显的反"C"型分布,采用正弯叶片后反“C”型压力分布的强度逐渐增大;流道内静压被重新分布,其中流道内径向压力梯度的改变对附面层和损失发展影响最大;正弯叶片引起的叶展中部损失的激增是导致总损失增大的主要因素,其中15°正弯叶栅改善流动、减小损失的效果最好。Experimental study was carried out for the effects of positive curved blade on surface static pressure in annular compressor cascades with large camber angles. The results showed that with the increase of curved angle, opposite C-shape static pressure distribution on suction surface of curved cascades became more acutely than straight blade. Static pressure was distributed in the flow passage of curved cascade, and the change of radial pressure grads affected maximally the development of boundary layer and loss. The acute increase of loss near mid-span was the main factor in the increase of total loss, and the positive curved blade with 15° had the greatest affect of improving flow and reducing total loss.

关 键 词：压气机叶栅 实聆研究 冲角 静压 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]