A design method combining three dimensional direct analysis with two dimensional inverse design is applied to a high load transonic compressor stage.First
the flow structures of the available stage ATS 2 (Advomced Transonic Stage) were analyzed by the 3D N S code in order to find out the existing problems.Secondly
aerodynamic numerical optimization is used to redesign the hub of the original rotor.Furthermore
the new flow structure is checked by using the 3D code.The numerical analysis indicates that the optimized stage is improved both in flow structure and performances
Low-Re Number Effects on the Performance of Some Fans and the Modified Design
Research on transient load for transonic compressor based on dynamic boundaries
Improved viscous inverse design method for three-dimensional turbomachinery blades
Design inquiry of an ultra-high-pressure-ratio component of multi-stage axial flow compressors
Numerical study on matching mechanism and efficiency ofpulse detonation combustor and impulse turbine
Related Author
GU Ming-hao
GUI Xing-ming
LI Shaobin
ZHANG Weiya
YANG Caiqiong
GUO Qiannan
李艾挺
朱阳历
Related Institution
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
Sichuan Gas Turbine Establishment,Aero Engine Corporation of China
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics