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Multi-scale nature of non-blade-order propagating flow disturbances in axial compressors

Chinese Journal of Aeronautics 2022年第9期35卷 129-142页

作者： Hao WANG Yan’gang WANG Hanru LIU Fei XUE Zhongnan WANG School of Power and Energy Northwestern Polytechnical UniversityXi'an 710072China College of Engineering and Physical Sciences University of BirminghamBirmingham B152TTUnited Kingdom

Non-blade-order flow disturbances, also referred to as pre-stall disturbances or tip flow unsteadiness, are closely related with compressor instabilities. The present work provides a comprehensive investigation on multi-scale nature of non-blade-order disturbances and the underlying flow physics in axial compressors. By applying full-annulus Unsteady Reynolds-Averaged Navier-Stokes(URANS) simulations, along with space–time correlation and spatial Fourier decomposition, to the disturbed pressure, the propagating feature of the non-blade-order disturbances is obtained. Further, a bridge between non-blade-order disturbances and the evolution of unsteady vortex has been set up. The results show that non-blade-order disturbances, featured as short-length-scale(35 modes across annulus), first appear as the occurrence of tip leakage vortex fluctuation, while the compressor still operates far from stall. Leading-edge radial vortex appears at near stall condition, and its movement induces a circumferential propagating disturbance overlaying on the one induced by oscillating tip leakage vortex. The interaction of the short-scale disturbances with a lowamplitude long-scale(of circumference) disturbance is observed, which results in disturbances with multiple scales of consecutive spatial modes, along with multiple frequency peaks in spectra. The compressor falls into stall as the circumferential nonuniform scattering of the leading-edge vortexes occurs. The densely-and sparsely-scattered leading-edge radial vortexes induce a high-amplitude long-scale(of circumference) disturbance , i.e. stall disturbance.

关键词： axial compressors Flow instabilities Multi-scale disturbances Stall Unsteady flow

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Modeling of 3-D Losses and Deviations in a Throughflow Analysis Tool

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Journal of Thermal Science 2007年第3期16卷 208-214页

作者： Jean-Fran■ois Simon OlivierLéonard Techspace Aero-Aerodynamic Group University

This contribution is dedicated to the modeling of the end-wall flows in a throughflow model for turbomachinery applications. The throughflow model is based on the Euler or Navier-Stokes equations solved by a Finite-Volume technique. Two approaches are presented for the end-wall modeling. The first one is based on an inviscid formulation with dedicated 3-D distributions of loss coefficient and deviation in the end-wall regions. The second approach is directly based on a viscous formulation with no-slip boundary condition along the annular end-walls and blade force modification in the region close to the end-walls. The throughflow results are compared to a series of 3-D Navier-Stokes calculations averaged in the circumferential direction. These 3-D calculations were performed on the three rotors of a low pressure axial compressor, for a series of tip clearance values.

关键词： throughflow losses deviations axial compressors

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Response and stabilization of a two-stage axial flow compressor restricted by rotating inlet distortion

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Chinese Journal of Aeronautics 2021年第9期34卷 72-82页

作者： Jia LI Xu DONG Dakun SUN Ruize XU Xiaofeng SUN Fluid and Acoustic Engineering Laboratory School of Energy and Power EngineeringBeihang UniversityBeijing 100083China

This paper considers effects of Rotating Inlet Distortion(RID)on a two-stage axial compressor and the stabilization effects of a casing treatment subjected to the considered *** multispool engines,the downstream compressor suffers a RID when the upstream fan/compressor is in rotating stall.A controlled rotating sectional screen upstream of the compressor was adopted to generate the RID in different intensities,and co-or counter spinning direction compared with the *** response of the compressor to inlet distortion was interpreted as the changes of stall *** show that there are two peaks for the stall margin degradation where the distortion screen rotates near 20%and 70%of the rotor’s rotational frequency,*** on the measurements taken during the pre-stall process,it is suggested that the two frequencies are associated with the eigen frequencies of the ***,the first is associated with a stall precursor that is suspected as an initial disturbance existing in compressor and the second is related to a spike-type stall *** last,a kind of Stall Precursor-Suppressed(SPS)casing treatment was applied to enhance the compressor stability in RID *** result indicates that the stall margin is improved by 6%at an average level and there is nearly no efficiency loss caused by the application of such casing treatment.

关键词： axial compressors Casing treatment Inlet distortion Stall margin Stall precursor

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Numerical study of camber and stagger angle effects on the aerodynamic performance of tandem-blade cascades

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Propulsion and Power Research 2018年第1期7卷 30-42页

作者： Behshad Ghazanfari Mahdi Nili-Ahmadabadi Ashkan Torabi-Farsani Mohammad Hossein Noorsalehi Department of Mechanical Engineering Isfahan University of TechnologyIsfahan ***Iran

Jet engine manufacturers and designers are seeking for lighter and smaller type of axial *** the aerodynamic characteristics of blades is carried out by controlling the boundary *** way to control the boundary layer is using tandem ***-blade cascades are capable of using highly loaded stages for axial compressors because they provide more works than single-blade *** other words,tandem blades help to achieve a specified total pressure ratio with less number of ***,one of the most important problems for researchers is to optimize the aerodynamic parameters of tandem *** the geometrical parameters of blades is a method to achieve this *** this work,the stagger and camber angle of each blade are first changed while the other geometrical parameters such as overall camber,total stagger angle,the axial overlap,percent pitch and chord ratio are ***,the overall camber angle of tandem blade is changed by increasing the difference between the stagger angle of the first and second blade while the type of two airfoils,axial overlap and percent pitch,overall chord length and overall stagger angle are *** aerodynamic performances of the generated tandem-blade cascades are obtained using two-dimensional numerical solution of *** this,a viscous turbulent flow solver is used for solving the Navier-Stokes *** these simulations,inlet Mach number is fixed to 0.6.

关键词： Tandem blade axial compressors Cascade Camber angle Stagger angle Flow deflection Loss coefficient

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Aeroelastic vibration analysis of a 1.5 stage compressor

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Propulsion and Power Research 2020年第1期9卷 26-36页

作者： Yun Zheng Qingzhe Gao Hui Yang Kang Xu School of Energy and Power Engineering Beihang UniversityBeijing100191China Collaborative Innovation Center for Advanced Aero-Engine Beijing100191China

Aeroelastic vibration problems are commonly found in modern compressors operating in off-design *** amplitude vibration could lead to high cycle fatigue(HCF)of blade and usually occurs in front stages of axial *** this study,the influence of tip gap size on aeroelastic stability is analyzed in a 1.5 stage compressor with an in-house fluid-structure interaction code.A three-dimensional unstructured finite-volume compressible flow solver is applied in the fluid domain and a structure dynamic solver with the modal superimposition method for blade motion is used in the structure *** tip clearances of 1%,2%and 3%of tip axial chord at maximum rotor loading conditions at off-design speeds are analyzed for aeroelastic *** tip leakage flow and vortex structure can be seen near the blade tip region at a larger tip gap *** aeroelastic stability of rotor blade at different tip gap sizes is mainly influenced by the 1st torsion mode,and the variation of aerodynamic damping is not *** intensity of the tip vortex and shock wave are the key factors affecting the aeroelastic stability of rotor when tip gap size increases.

关键词： Aeroelastic vibration problems axial compressors Tip gap size Aeroelastic stability Tip vortex Shock wave

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