冲角对正弯曲叶片扩压叶栅气动性能的影响  

Influence of incidence on aerodynamic performance of compressor cascade with positive curved blade

作　　者：王会社[1] 袁新[1] 钟兢军[2] 王仲奇[2] 马征 

机构地区：[1]清华大学热能工程系,北京100084 [2]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001 [3]中国华录工程公司,陕西西安710065

出　　处：《推进技术》2003年第2期130-134,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(50076009;50076019);973(G1999022306;G1999022307);全国优秀博士学位论文作者专项基金(199932)

摘　　要：为了研究冲角对正弯曲叶片压气机叶栅气动性能的影响,在平面叶栅低速风洞上,对具有可控扩散叶型(CDA)的直叶片,正弯曲15°和20°弯曲叶片压气机叶栅在0°,±6°和±10°冲角下进行了实验,获得了不同冲角下不同弯曲角度叶栅出口流场的能量损失系数和叶片表面静压系数等的分布。与直叶栅相比,叶片正弯曲后叶栅总损失在所有冲角下均得到了降低,在正冲角下,叶栅端部流动状况得到改善,在负冲角下,叶栅流道中的流动相对于直叶栅改善不明显。直叶栅在10°冲角下发生了遍布整个流道的分离流动,而正弯曲叶片的采用则削弱了流动的分离。In order to investigate the influence of incidence on the aerodynamic performance of the compressor cascade with positive curved blades, experiments were conducted in a low speed wind tunnel with planar cascade. Rectangle compressor stator cascades constituted by three different positive curved blades with controlled diffusion airfoils were tested. These include; straight blades, positive curved angle 15° and 20° blades. The distribution of energy loss coefficient at all cascade exits and static pressure coefficient on blade surfaces were acquired. The results show that the total losses of the curved blade cascades are reduced in all test incidences. In positive incidence, the endwall flow of curved blade cascades is improved, and in negative incidence it s not so obvious. At the incidence degree of 10°, the separation of flow took place everywhere in linear cascade, and so weakened in curved blade cascades.

关 键 词：压气机叶片 压气机叶栅 叶型 弯曲 气动特性 

分 类 号：V232.41[航空宇航科学与技术—航空宇航推进理论与工程]