The method for 3 D design of fans or pumps in the present paper is presented which is based on the solutions of a quasi 3D inverse method and a 3D N S solver.At beginning the flow rate
the pressure ratio and the geometry of meridian pattern were given. The span height distributions of inlet and exit pitch wise averaged flow angles (or blade circulation) of the blade channel were obtained by the preliminary calculations.They are served to be the target parameters of the present calculation.Successively using a quasi 3D inverse method and a N S solver
a 3 D blade configuration can be obtained.As an example
Regularization method for subsonic hovering rotor sound source reconstruction
A viscous inverse problem method for turbomachinery three-dimensional blade profile
Similarity solutions and approximation solutions of velocity and temperature in laminar boundary layer of subsonic and supersonic wedge flows
Half-inverse problem for design of S-shaped compressor transition duct
Study and numerical calculation wall streamline distributions for hypersonic vehicle according to Euler equation
Related Author
赵庆贺
李晓东
NING Fang-fei
JIA Xin-liang
JU Peng-fei
ZHAO Guo-chang
DU Xia
SONG Li-ping
Related Institution
北京航空航天大学 能源与动力工程学院
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamic, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics
Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University
Faculty of Aerospace Engineering, Shenyang Aerospace University
Institute of High Education, Shenyang Aerospace University