进气道内加装导流体对低压转子振动特性影响分析  

Analysis of low-pressure compressor rotor vibration characteristics induced by inlet guide vane

作　　者：侯安平[1] 李秋实[1] 周盛[1] 唐昭勇[2] 冯维林[2] 吴承杰[2] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京100083 [2]成都飞机设计研究所,四川成都610500

出　　处：《航空动力学报》2006年第4期686-692,共7页Journal of Aerospace Power

基　　金：国家自然科学基金资助(10477002)

摘　　要：对发动机进口前进气道管道内安装导流体后可能导致的压气机低压转子流动诱发振动现象进行了评估。通过定常和非定常数值模拟发现,以导流体叶片数决定的通过频率对发动机低压转子振动特性的影响较小;同时由于导流体尾迹内部脱落涡强度太低,其脱落频率也不会对发动机低压转子振动特性产生影响。计算结果表明,本算例中导流体的叶型设计和安装位置是合理的。This paper estimated the possibility of flow induced vibration in low-pressure compressor rotor with inlet guide vane. Through steady and unsteady numerical simulation, it was found that blade passage frequency of the guide vanes influences little on the vibration characteristics of the low-pressure compressor rotor. Moreover, because the intensity of vortex shedding in the wake of the guide vane is too weak,it＇s frequency has no influence on the vibration characteristics of the low-pressure compressor rotor. The computational result shows that both the design of airfoils and the location of installation are reasonable.

关 键 词：航空 航天推进系统 导流体 振动特性 进气道 

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]