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Evolution of Unsteady Flow near Rotor Tip during stall inception

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Journal of Thermal Science 2011年第4期20卷 294-303页

作者： Shaojuan Geng Feng Lin Jingyi Chen Chaoqun Nie Institute of Engineering Thermophysics Chinese Academy of Sciences RO. Box 2706 Beijing 100190 China

Previously the features of circumferential propagation of self-induced tip leakage flow unsteadiness for a low speed isolated axial compressor rotor in the authors' laboratory were discovered and investigated via numerical simulation,which only occurs below a critical stable flow point that is close to but not yet at the stall *** in this paper,the detailed investigation on evolution of tip leakage flow during the throttling process into spike rotating stall was conducted by adopting the valve-throttling *** this process,the development of the circumferential propagation of tip leakage flow unsteadiness was especially focused *** to the unsteady characteristics of pressure signals,the evolvement of compressor flow field can be classified into four *** compressor throttled,the oscillation frequency of self-induced unsteady tip leakage flow decreased gradually,and thus resulted in the decrease of its circumferential propagation *** circumferential propagation of self-induced tip leakage flow unsteadiness is closely related with rotating *** the forward spillage of tip leakage flow at the leading edge occurred,the spike type rotating stall was *** flow struc-tures were given in the paper.

关键词： Axial compressor stall inception tip leakage flow rotating instability numerical simulation

Numerical Investigation of the Unsteady Tip Leakage Flow and Rotating stall inception in a Transonic Compressor

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Journal of Thermal Science 2010年第4期19卷 310-317页

作者： Yanfeng Zhang Xingen Lu Wuli Chu Junqiang Zhu School of Power and Energy Northwestern Polytechnical University Xi'an Shaanxi 710072 China Institute of Engineering Thermophysics Chinese Academy of Sciences Beijing 100190 China

It is well known that tip leakage flow has a strong effect on the compressor performance and stability. This paper reports on a numerical investigation of detailed flow structures in an isolated transonic compressor rotor-NASA Rotor 37 at near stall and stalled conditions aimed at improving understanding of changes in 3D tip leakage flow structures with rotating stall *** and unsteady 3D Navier-Stokes analyses were conducted to investigate flow structures in the same *** steady analysis,the predicted results agree well with the experimental data for the estimation of compressor rotor global *** unsteady flow analysis, the unsteady flow nature caused by the breakdown of the tip leakage vortex in blade tip region in the transonic compressor rotor at near stall condition has been captured with a single blade *** the other hand, the time-accurate unsteady computations of multi-blade passage at near stall condition indicate that the unsteady breakdown of the tip leakage vortex triggered the short length-scale-spike type rotating stall inception at blade tip *** was the forward spillage of the tip leakage flow at blade leading edge resulting in the spike stall inception. As the mass flow ratio is decreased,the rotating stall cell was further developed in the blade passage.

关键词： transonic axial-flow compressor tip clearance flow stall inception unsteadiness

Prediction of stall inception in multi-stage compressors based on an eigenvalue approach

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Science China(Technological Sciences) 2017年第8期60卷 1132-1143页

作者： CHENG FanJie SUN DaKun DONG Xu SUN XiaoFeng School of Energy and Power Engineering Beihang University Beijing 100191 China

A stability model for multi-stage compressor is developed on the basis of the eigenvalue *** model assumes that the unsteady flow field can be decomposed into pressure,vortex and entropy ***,a linear cascade of blades is modeled by three-dimensional semi-actuator disk theory and the characteristics of steady flow field are also considered in the present *** connection between the analytical solution for stator,rotor and gap can be established by applying mode matching approach,the relevant stability equation can be expressed in the form of matrix,while the compressor system stability can be judged by the imaginary part of the matrix *** capacity of the stall inception model to predict the stall inception point of multi-stage compressor is assessed against the experimental data of National Aeronautics and Space Administration(NASA) two stage *** theoretical results show that this model can predict the stall onset points of a two-stage fan at different operating speeds with a reasonable accuracy.

关键词： multi-stage compressor unsteady flow rotating stall stability model stall inception

Experimental Research on Inlet Steady Swirl Distortion in an Axial Compressor with Non-Uniform Tip Clearance

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Journal of Thermal Science 2023年第1期32卷 286-296页

作者： XU Rong HU Jun WANG Xuegao JIANG Chao LI Wenyu College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China

The inlet swirl distortion and non-uniform tip clearance have great effects on aero-engine performance and stall *** this paper,the effects of paired swirl distortion on the aerodynamic stability and stall inception of a single stage axial compressor with non-uniform tip clearance are quantitatively analyzed by using the swirl distortion *** experimental results show that the paired swirl distortion dominated by co-rotating swirl improves the stability of the axial *** a single-stage axial compressor with eccentricity of 100%,the stall inception starts at the maximum tip clearance with clean *** initial position of the stall inception is determined by the maximum tip clearance when the small intensity paired swirl distortion exists at the compressor *** the swirl intensity increases,it shifts towards the position of the counter rotating swirl vortex *** inlet swirl will not change the type of stall inception.

关键词： steady swirl distortion non-uniform tip clearance stall inception experiment research compressor performance

SIMULATION OF ACTIVE CONTROL OF ROTATING stall IN AXIAL COMPRESSOR

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Chinese Journal of Aeronautics 1997年第3期10卷 58-62页

作者： Xu Gang (Thermal Engineering Department, Tsinghua University, Beijing, 100084, China) Li Jun, Zhu Junqiang, Liu Zhiwei (Aeronautics & Thermal Engineering Department, Northwestern Polytechnic University, Xi′an, 710072, China)

A theoretical system has been developed to simulate the control of rotating stall. Circulating disturbance was appended to the system to suppress the developing of rotating wave. The control system has slight influence on the systems critical B coefficient B cr . Self adaptive sector has been inserted into the proportion feed back control system to fit the nonlinear compressor system.

关键词： active control rotating stall turbocompressors stall inception

Effect of system response on partial surge initiated instability in a transonic axial flow compressor

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Chinese Journal of Aeronautics 2022年第2期35卷 117-127页

作者： Tianyu PAN Zhaoqi YAN Dakun SUN Simin LI Mengzong ZHENG Qiushi LI Reserach Institute of Aero-Engine Beihang UniversityBeijing 100083China School of Energy and Power Engineering Beihang UniversityBeijing 100083China Key Laboratory of Fluid and Power Machinery Ministry of EducationXihua UniversityChengdu 610039China

Partial surge is a type of instability inception in transonic compressors and occurs in the form of axisymmetric low-frequency disturbances localized in the hub *** studies illustrate that the frequency of partial surge is set by the Helmholtz frequency of the entire system,which motivates to propose a hypothesis that the system response performs an important role in the formation of partial *** further verification,a series of experiments are conducted to explore the link between the propagating of the partial surge and the system feedback in this *** the first case,an additional test point is set on the wall of the plenum to detect the system *** the flow behaviors inside the plenum with the disturbances in the rotor tip and stator hub/tip regions,the effects of the system feedback on the occurrence of the continuous disturbances and the rotating stall cells are *** the second case,a screen is mounted at the compressor outlet to prevent positive feedback from the *** experimental results demonstrate that in the absence of system feedback,it is the occurrence of spike-type stall inception that leads to the flow instability instead of that of partial *** addition,three flow phenomena in the second case are discussed,including the occurrence of the single pulse,the unstable process during the stall evolution and the switch of instability inception.

关键词： Partial surge Plenum amplification Rotating stall System response stall inception Transonic compressor