| 进口畸变条件下轴流压气机转子内流的PIV研究 |
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| 引用本文： | 李茂义,陆亚钧,弓志强,袁巍.进口畸变条件下轴流压气机转子内流的PIV研究[J].航空动力学报,2006,21(3):461-466. |
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| 作者姓名： | 李茂义 陆亚钧 弓志强 袁巍 |
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| 作者单位： | 北京航空航天大学,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 |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 摘 要： | 用50%堵塞比的插板畸变屏模拟低速轴流压气机进口流场畸变,用PIV(粒子图像速度场仪,ParticleImage Velocimetry)技术测量均匀和畸变进气条件下压气机转子叶片通道内的流场结构.实验表明,进气畸变条件下压气机流场在转子叶片通道内不同的周向位置会产生四种不同的流动结构状态,同时,进气畸变大大增加了漩涡扰动、流动亏损和转子叶排气流分离的强度,这样必然会对压气机的性能产生很大的影响.实验也验证了经典平行压气机理论的缺陷.
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| 关 键 词： | 航空、航天推进系统 进气畸变 轴流压气机 转子叶片通道 PIV技术 流场结构 |
| 文章编号： | 1000-8055(2006)03-0461-06 |
| 收稿时间： | 2005/6/11 0:00:00 |
| 修稿时间： | 2005年6月11日 |
PIV Investigation of the Internal Flow in an Axial Flow Compressor Rotor under Inlet Distortion |
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| LI Mao-yi,LU Ya-jun,GONG Zhi-qiang and YUAN Wei.PIV Investigation of the Internal Flow in an Axial Flow Compressor Rotor under Inlet Distortion[J].Journal of Aerospace Power,2006,21(3):461-466. |
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| Authors: | LI Mao-yi LU Ya-jun GONG Zhi-qiang and YUAN Wei |
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| Institution: | National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | Flow field structure in the rotor blade passage of a low speed axial flow compressor both under uniform inlet flow and distorted flow simulated by adding baffles with 50% blocking ratio was investigated using PIV(Particle Image Velocimetry) technique.Experimental results indicate that there are four different flow field structure types in the compressor rotor passage at different circumferential positions under inlet distortion.Inlet distortion makes the intensity of vortex disturbance,velocity decrement and separation in the rotor passage rise greatly.This will affect the performance of compressor heavily.The experiment also testifies the limitation of the classical parallel compressor theory. |
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| Keywords: | aerospace propulsion system inlet distortion axial flow compressor rotor blade passage PIV technique flow field structure |
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