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| 1 | Experimental Study of Corner Stall in a Linear Compressor Cascade显示文摘In order to gain a better knowledge of the mechanisms and to calibrate computational fluid dynamics (CFD) tools including both Reynolds-averaged Navier-Stokes (RANS) and large eddy simulation (LES),a detailed and accurate experimental study of corner stall in a linear compressor cascade has been carried out.Data are taken at a Reynolds number of 382 000 based on blade chord and inlet velocity.At first,inlet flow boundary layer is surveyed using hot-wire anemometry.Then in order to investigate the effects of incidence,measurements are acquired at five incidences,including static pressures on both blade and endwall surfaces measured by pressure taps and the total pressure losses of outlet flow measured by a five-hole pressure probe.The maximum losses as well as the extent of losses of the corner stall are presented as a function of the investigated incidences. | MA Wei OTTAVY Xavier LU Lipeng LEBOEUF Francis GAO Feng | 2011 | Chinese Journal of Aeronautics2011，24，3： | 8 |
| 2 | 根部开槽对叶栅三维角区分离的控制研究显示文摘三维角区分离是压气机静子叶栅中固有的流动结构,对压气机性能有着重要的影响。本文对一PVD叶栅和一NACA65叶栅,在分析其通道内流动机理的基础上,提出了在叶片根部从压力面向吸力面开槽的控制角区分离的方法。数值研究了槽道出口位置对PVD叶栅性能及角区分离的控制作用,发现在保持槽道其他参数不变的情况下,存在一最优位置使得叶栅攻角特性最优;结合计算及实验测量的方法,验证了NACA65叶栅中叶根开槽控制角区分离的有效性。两个叶栅研究结果表明:叶根开槽可有效控制角区分离,减小叶栅损失,增大叶栅扩压能力,拓宽叶栅可用攻角范围。 | 孙槿静 柳阳威 陆利蓬 OTTAVY Xavier | 2019 | 工程热物理学报2019，40，12： | 6 |
| 3 | Control of Corner Separation by Optimized Slot Configuration in a Linear Compressor Cascade显示文摘为控制压气机叶片吸力面与端壁处所形成的三维角区分离,本文在叶根处引入了从压力面到吸力面的槽道来控制角区分离流动。基于利用优化算法对叶根处槽道几何的优化结果,本文通过数值模拟和实验来分析槽道在不同进口攻角下对角区分离的控制效果。本文通过对比原始和开槽叶栅中总压损失、静压升和三维角区分离特征表明叶根处引入的槽道对角区分离有明显的控制效果。 | Jinjing Sun Yangwei Liu Lipeng Lu Xavier OTTAVY | 2016 | 风机技术2016，58，6： | 4 |
| 4 | Experimental investigation of flow field in a laboratory-scale compressor显示文摘The inner flow environment of turbomachinery presents strong three-dimensional, rotational, and unsteady characteristics. Consequently, a deep understanding of these flow phenomena will be the prerequisite to establish a state-of-the-art design system of turbomachinery. Currently the development of more accurate turbulence models and CFD tools is in urgent need for a high-quality database for validation, especially the advanced CFD tools, such as large eddy simulation(LES). Under this circumstance, this paper presents a detailed experimental investigation on the 3D unsteady flow field inside a laboratory-scale isolated-rotor with multiple advanced measurement techniques, including traditional aerodynamic probes, hotwire probes, unsteady endwall static pressure measurement, and stereo particle image velocimetry(SPIV). The inlet boundary layer profile is measured with both hotwire probe and aerodynamic probe. The steady and unsteady flow fields at the outlet of the rotor are measured with a mini five-hole probe and a single-slanted hotwire probe. The instantaneous flow field in the rotor tip region inside the passage is captured with SPIV,and then a statistical analysis of the spatial distribution of the instantaneous tip leakage vortex/flow is performed to understand its dynamic characteristics. Besides these, the uncertainty analysis of each measurement technique is described. This database is quite sufficient to validate the advanced numerical simulation with LES. The identification process of the tip leakage vortex core in the instantaneous frames obtained from SPIV is performed deliberately. It is concluded that the ensemble-averaged flow field could not represent the tip leakage vortex strength and the trajectory trace. The development of the tip leakage vortex could be clearly cataloged into three phasesaccording to their statistical spatial distribution. The streamwise velocity loss induced by the tip leakage flow increases until the splitting process is weak and the turbulent mixing phase is dominant. | Ma Hongwei Wei Wei Xavier Ottavy | 2017 | Chinese Journal of Aeronautics2017，30，1： | 3 |
| 5 | Effect of an adverse pressure gradient on the streamwise Reynolds stress profile maxima in a turbulent boundary layer显示文摘It is widely accepted that in a turbulent boundary layer (TBL) with adverse pressure gradient (APG) an outer peak usually appears in the profile of streamwise Reynolds stress. However, the effect of APG on this outer peak is not clearly understood. In this paper, the effect of APG is analysed using the numerical and experimental results in the literature. Because the effect of upstream flow is inherent in the TBL, we first analyse this effect in TBLs with zero pressure gradient on flat plates. Under the individual effect of upstream flow, an outer peak already appears in the profile of streamwise Reynolds stress when the TBL continues developing in the streamwise direction. The APG accelerates the appearance of the outer peak, instead of being a trigger. | Wei Ma Xavier Ottavy Li-Peng Lu Francis Leboeuf | 2013 | Acta Mechanica Sinica2013，29，3： | 1 |
| 6 | Parameter study on numerical simulation of corner separation in LMFA-NACA65 linear compressor cascade显示文摘Large-eddy simulation(LES) is compared with experiment and Reynolds-averaged Navier-Stokes(RANS), and LES is shown to be superior to RANS in reproducing corner separation in the LMFA-NACA65 linear compressor cascade, in terms of surface limiting streamlines,blade pressure coefficient, total pressure losses and blade suction side boundary layer profiles. However, LES is too expensive to conduct an influencing parameter study of the corner separation.RANS approach, despite over-predicting the corner separation, gives reasonable descriptions of the corner separated flow, and is thus selected to conduct a parametric study in this paper. Two kinds of influencing parameters on corner separation, numerical and physical parameters, are analyzed and discussed: second order spatial scheme is necessary for a RANS simulation; incidence angle and inflow boundary layer thickness are found to show the most significant influences on the corner separation among the parameters studied; unsteady RANS with the imposed inflow unsteadiness(inflow angle varying sinusoidally with fluctuating amplitude of 0.92°) does not show any non-linear effect on the corner separation. | Gao Feng Ma Wei Sun Jinjing Jérome Boudet Xavier Ottavy Liu Yangwei Lu Lipeng Shao Liang | 2017 | Chinese Journal of Aeronautics2017，30，1： | 0 |
| 7 | L2F Anemometry Measurements of the Inter-Row FlowField Within a Transonic Axial Compressor Providedwith Curved Windows显示文摘INTRODUCTIONMultibladerowcalculationscanbeperformedusingsteady3DNScodesprovidedthatassumptionsaremadeforthecouplingofbladerows.Thesocalledmixing--planeapproachneedsthetangentialaveragesofflowquantitiesattheinterfaceplanebetweenadjacentbladerows.Butth... | Xavier Ottavy Isabelle Trebinjac Andre Vouillarmet(Laboratoire de Mecanique des Fluides et d’Acoustique UMR CNRS 5509/ECL/UCB Lyon IEcole Centrale de Lyon, 69131 Ecully Cedex, France) | 1999 | Journal of Thermal Science1999，8，3： | 0 |
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