叶尖间隙对弹用跨声速及亚声速压气机动叶的影响  

Influence of Tip Clearance Size on the Performance of Transonic and Subsonic Compressor Rotor for Missiles

作　　者：陈健 闫学慧[2] 陈忠良 Chen Jian;Yan Xuehui;Chen Zhongliang(AECC Xi’an Aero-engine LTD,Xi’an 710021,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]中国航发西安航空发动机有限公司,西安710021 [2]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2020年第2期39-43,114,共6页Tactical Missile Technology

摘　　要：为了平衡弹用涡轮发动机的制造成本与气动性能,采用三维数值模拟方法,研究了叶尖间隙高度对跨声速及亚声速压气机动叶的影响。结果表明,叶尖间隙对跨声速与亚声速压气机动叶影响有显著差异,其中,对亚声速动叶的影响可以忽略,但对跨声速叶片影响很大。对于跨声速叶片,随着间隙增大,叶片增压比、最高效率逐步减小,熵增区域也发生了显著改变。因此,相比亚声速动叶,跨声速动叶叶尖间隙的公差范围需更为严格。To balance the cost and the performance of a missile engine compressor,the influence of the tip clearance height of rotor on a transonic and a subsonic compressor is investigated by three dimensional numerical simulation. Results show that the influences of tip clearance heights on a transonic blade and a subsonic blade are totally different,and the influence can be neglected for subsonic blade while it is substantial for a transonic blade. To a transonic blade,pressure ratio and max efficiency drops when the tip clearance increases and the distribution of entropy has changed greatly. In conclusion,the clearance tolerance of a transonic rotor must be much more strict compared to that of a subsonic rotor.

关 键 词：导弹发动机 压气机 叶尖间隙 跨声速 亚声速 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]