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不同形式插板对压气机影响仿真与实验

Experimental and Simulation Experimental on Influence of Different Forms of Baffles on Compressor

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【作者】 王相宇; 屠宝锋; 任智博; 施磊; 梁彩云;

【Author】 WANG Xiangyu;TU Baofeng;REN Zhibo;SHI Lei;LIANG Caiyun;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics;AECC Shenyang Engine Research Institute;Taihang Laboratory;

【通讯作者】 屠宝锋;

【机构】 南京航空航天大学能源与动力学院; 中国航发沈阳发动机研究所; 太行实验室;

【摘要】 为研究稳动态畸变不同比例对压气机气动性能及稳定性的影响机理和规律,分别采用均匀齿、均匀孔、弦月式3种不同形式插板进行插板压气机联合实验与仿真。结果表明:相较于弦月式插板,均匀齿插板与均匀孔插板在多种深度下均能起到扩大稳动态畸变比例的作用;3种形式插板均会导致压气机压比与效率下降,失速流量增大,相同深度下,弦月式插板影响最大,均匀孔插板次之,均匀齿插板最小。在综合畸变指数相差不大时,动态畸变占比增加会导致压气机易失速。双级低速轴流压气机失稳的原因主要是因为静子角区分离与转子叶尖泄漏流。不同情况的畸变会改变失速先兆出现的位置以及失速团的传播速度,但是不会改变失速先兆形式。

【Abstract】 In order to study the mechanism and law of the influence of different steady and dynamic distortion ratios on the aerodynamic performance and stability of the compressor,three different forms of baffles,such as uniform tooth baffle,uniform hole baffle and normal baffle,are used to carry out the joint experiment of insert plate compressor.The experimental results show that the uniform tooth baffle and the uniform hole baffle can play a role in expanding the stable and dynamic distortion ratio at most depths compared with the normal baffle;the three types of baffles will lead to the decrease of compressor pressure ratio and efficiency,and the increase of stall flow rate,at the same depth,the normal baffle has the greatest influence,followed by the uniform hole baffle,and the uniform tooth baffle is the smallest;when the comprehensive distortion index is not much different,the increase of the proportion of dynamic distortion leads to the stall of the compressor.The main reasons for the instability of a two-stage low-speed axial compressor are stator corner separation and rotor tip leakage flow.The distortion of different conditions will change the location of the stall inception and the propagation speed of the stall cell,but will not change the form of the stall inception.

【基金】 国家科技重大专项(J2019-I-0011-0011)
  • 【文献出处】 海军航空大学学报 ,Journal of Naval Aviation University , 编辑部邮箱 ,2025年05期
  • 【分类号】V233
  • 【下载频次】30
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