A method has been developed for calculation of three-dimensional flows in aeroengine combustor including diffuser and flametube
inner and outer annuluses.The 3D body-fitting grid has been generated to deal with the complex geometry of the combustor.The non-staged grid scheme and k-ε turbulence model has been adopted.The mass flowing thought primary holes
dilution holes and film cooling holes has been calculated.The calculated results are consistent reasonably with the experimental measurements.
Large eddy simulation of supersonic jet mixing flow
Study on improvement of the compressor anti-swirl distortion capacity with bowed stator
Comparison and analysis of WENO schemes base on supersonic boundary layer transition
Numerical investigation of impressible turbulent flows past airfoils
Orthogonal optimal design of solid fuel formulation for HO/HTPB hybrid rocket motor
Related Author
朱志斌
程晓丽
潘宏禄
TU Bao-feng
LIU Hua
HU Jun
LIU Chao-yang
WANG Zhen-guo
Related Institution
中国航天科技集团有限公司 中国航天空气动力技术研究院
Collaborative Innovation Center for Advanced Aero-Engine
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics
College of Aerospace Science and Engineering, National University of Defense Technology
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics