压气机线性振荡叶栅气弹试验研究(一)：非定常气动响应  

Experimental Study on Aeroelasticity in Linear Oscillating Compressor Cascade.PartⅠ:Unsteady Aerodynamic Response

作　　者：杨慧[1] 何力[2] 王延荣[1] 

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数值仿真研究中心,北京100083 [2]牛津大学工程科学院,英国牛津OX1 3PJ

出　　处：《航空学报》2008年第4期795-803,共9页Acta Aeronautica et Astronautica Sinica

摘　　要：为了加强对叶轮机三维气动弹性机理的理解,为数值模拟方法提供试验验证数据,开展了压气机线性叶栅气动弹性试验研究。本研究分为两部分,本文为第1部分,研究压气机线性振荡叶栅的气弹稳定性,第2部分重点辨别叶尖间隙对此振荡叶栅气弹稳定性的影响。组建了线性叶栅试验台,其试验段由7个真实可控扩散叶型组成,中间叶片由凸轮机构驱动模拟三维一阶弯曲振动。使用外置压力传感器在6个叶高处测量叶片表面的定常压力分布和3个折合频率下叶片表面非定常压力分布。由管传递函数修正连接管造成的非定常信号失真。运用影响系数法构造协调叶栅任意叶片间相位角下的非定常气动响应结果。试验结果表明:非定常气动响应具有完全的三维特征;折合频率和叶片间相位角对叶栅的气动弹性稳定性具有决定性影响。An experiment is carried out to enhance the understanding of three-dimensional（3D） blade aeroelastic mechanisms and to produce the experimental data for the validation of numerical methods.Forming the first part of the two-part series,the experimental study on the aeroelastic stability of the compress oscillating cascade is presented.The tip-clearance effects on the aeroelastic response of the same cascade are identified in part Ⅱ.A linear cascade experiment rig is developed.It consistes of seven prismatic controlled diffusion blades.The middle blade is driven by the crank bar mechanism to simulate a 3D bending/flapping oscillating mode.Steady and unsteady pressure measurements are performed at six spanwise sections for three reduced frequencies.Off-board pressure transducers are utilized with a transfer-function method to correct tubing errors.The tuned cascade results are constructed by using the influence coefficient method.The results illustrate the fully 3D unsteady behaviour and the significant influence of reduced frequency and inter-blade phase angle on the unsteady aerodynamic response.

关 键 词：航空、航天推进系统 流体-固体耦合振动 影响系数法 气动阻尼 叶片间相位角 折合频率 三维叶片振动 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程] V216.24