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Resilient control of flexible hypersonic vehicles against unmatched distributed faults
《Chinese Journal of Aeronautics》2024年第5期60-70,共11页Dong ZHAO Wenjing REN 
This work was supported by the National Natural Science Foundation of China(Nos.62203002 and 62203148);Natural Science Foundation of Anhui Province,China(Nos.2208085QF204 and 2208085QF203);the Open Project Program of Fujian Provincial Key Laboratory of Intelligent Identification and Control of Complex Dynamic System,China(No.2022A0001);the Fundamental Research Funds for the Central Universities,China(No.JZ2022HGTA0346).
This paper studies a robust fault compensation and vibration suppression problem of flexible hypersonic vehicles.The controlled plant is represented by a cascade system composed of a nonlinear Ordinary Differential Eq...
关键词：Flexible hypersonic vehicles ODE-EBBE cascade Robust exponential stability Unmatched distributed fault compensation Vibration suppression 
Numerical and experimental investigation of quantitative relationship between secondary flow intensity and inviscid blade force in axial compressors
《Chinese Journal of Aeronautics》2023年第10期101-111,共11页Chenghua ZHOU Zixuan YUE Hanwen GUO Xiwu LIU Donghai JIN Xingmin GUI 
the National Science and Technology Major Project,China(Nos.2017-I-0005-0006&2019-II-0020-0041).
The secondary flow attracts wide concerns in the aeroengine compressors since it has become one of the major loss sources in modern high-performance compressors.But the research about the quantitative relationship bet...
关键词：Axial compressor cascade Corner separation Spanwise inviscid blade force Secondary flow intensity Quantitative correlation 
Control of squealer-tip leakage flow with perforated-rib coolant injection in an axial turbine cascade
《Chinese Journal of Aeronautics》2023年第8期54-73,共20页Shengchang ZHANG Qinqin WANG Xiaoming TAN Jingzhou ZHANG 
supported by the National Science and Technology Major Project,China(No.2017-III-0001-0025);the Interdisciplinary Innovation Foundation for Graduates at Nanjing University of Aeronautics and Astronautics in China(No.KXKCXJJ202002).
A novel perforated-rib configuration is proposed for controlling the tip leakage flow at the rotor tip of an axial turbine.Three perforated-rib layouts are considered,wherein a perforated rib is installed at(A)the Suc...
关键词：AERODYNAMICS Perforatedrib Squealer tip Tip injection Tipleakageflow 
Method for utilizing PIV to investigate high curvature and acceleration boundary layer flows around the compressor blade leading edge
《Chinese Journal of Aeronautics》2022年第12期72-88,共17页Baojie LIU Xiaobin XU Xianjun YU Guangfeng AN 
funded by the National Natural Science Foundation of China(Nos.51790511 and 51806004);the National Science and Technology Major Project,China(No.2017-II-0001-0013).
Particle Image Velocimetry(PIV)is a well-developed and contactless technique in experimental fluid mechanics,but the strong velocity gradient and streamline curvature near the wall substantially limits its accuracy im...
关键词：Boundary layer measurement Compressor blade leading edge Mirror interchange method Particle image velocimetry Planar cascade experiment 
A reduced order model for coupled mode cascade flutter analysis被引量：1
《Chinese Journal of Aeronautics》2022年第10期176-182,共7页Huang HUANG Xinkai JIA Jia REN Bochao CAO Dingxi WANG Xiuquan HUANG 
supported by the National Science and Technology Major Project, China (No. 2017-II-0009-0023);the Aeronautical Science Foundation of China(No. 2020Z039053004);the Fundamental Research Funds for the Central Universities, China (No. 3102019OQD701)
A Reduced Order Model(ROM)based analysis method for turbomachinery cascade coupled mode flutter is presented in this paper.The unsteady aerodynamic model is established by a system identification technique combined wi...
关键词：Aerodynamic influence coefficients Chirp signal Coupled mode flutter Eigenvalue problem Reduced order model 
Investigation of flow unsteadiness in a highly-loaded compressor cascade using a dynamic mode decomposition method被引量：3
《Chinese Journal of Aeronautics》2022年第5期275-290,共16页Guangyao AN Yanhui WU Jinhua LANG Zhiyang CHEN Xiaobing ZHOU 
supports of National Natural Science Foundation of China(Nos.51790512,52176045);the National Major Science and technology Project of China(No.J2017-Ⅱ-0010-0024);the Innovation Foundation for Doctor Dissertation of Northwestern Polytechnical University,China(No.CX201911)。
Unsteady flow in the hub endwall region has long been a hot topic in the turbomachinery community.However important it is to the performance of the whole engine,the coherent unsteady flow phenomena are still not well ...
关键词：CASCADE COMPRESSOR Dynamic Mode Decomposition(DMD) ENDWALL Unsteady flow Vortex breakdown 
A combined application of micro-vortex generator and boundary layer suction in a high-load compressor cascade被引量：14
《Chinese Journal of Aeronautics》2019年第5期1171-1183,共13页Shan MA Wuli CHU Haoguang ZHANG Xiangjun LI Haiyang KUANG 
co-supported by the National Natural Science Foundation of China(Grants Nos.51576162 and 51536006)
In the current study, the effects of a combined application between micro-vortex generator and boundary layer suction on the flow characteristics of a high-load compressor cascade are investigated. The micro-vortex ge...
关键词：Boundary layer SUCTION Flow control strategies High-load COMPRESSOR CASCADE Numerical simulations VORTEX generators 
Influence of coupled boundary layer suction and bowed blade on flow field and performance of a diffusion cascade被引量：13
《Chinese Journal of Aeronautics》2017年第1期249-263,共15页Cao Zhiyuan Liu Bo Zhang Ting Yang Xiqiong Chen Pingping 
supported by China Postdoctoral Science Foundation;a key project of the National Natural Science Foundation of China (No. 51236006)
Based on the investigation of mid-span local boundary layer suction and positive bowed cascade, a coupled local tailored boundary layer suction and positive bowed blade method is developed to improve the performance o...
关键词：Axial compressor Boundary layer suction Bowed blade Corner separation Coupled method Passage vortex 
Parameter study on numerical simulation of corner separation in LMFA-NACA65 linear compressor cascade被引量：2
《Chinese Journal of Aeronautics》2017年第1期15-30,共16页Gao Feng Ma Wei Sun Jinjing Jérome Boudet Xavier Ottavy Liu Yangwei Lu Lipeng Shao Liang 
funded by the Sino-French project AXIOOM (funding: NSFC and ANR);the supports from NSFC (Nos. 51420105008, 51376001, 51506121 and 51676007);performed using HPC resources from GENCICINES (No.2014-2a6081)
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 casca...
关键词：Corner separation Influencing parameter LES Linear compressor cascade RANS 
Numerical study of corner separation in a linear compressor cascade using various turbulence models被引量：14
《Chinese Journal of Aeronautics》2016年第3期639-652,共14页Liu Yangwei Yan Hao Liu Yingjie Lu Lipeng Li Qiushi 
supported by the National Natural Science Foundation of China(No.51376001,No.51420105008,No.51306013,No.51136003);the National Basic Research Program of China(2012CB720205,2014CB046405);the Beijing Higher Education Young Elite Teacher Project;the Fundamental Research Funds for the Central Universities;supported by the Innovation Foundation of BUAA for Ph.D.Graduates
Three-dimensional corner separation is a common phenomenon that significantly affects compressor performance. Turbulence model is still a weakness for RANS method on predicting corner separation flow accurately. In th...
关键词：Compressor cascade Corner separation Turbomachinery CFD Turbulence anisotropy Turbulence models 
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