Optimization Design Of High-loaded Supersonic Compressor Rotor Blade

For compressor, a higher single stage pressure ratio can effectively reduce both the size and weight of the engine, thus raise the thrust weight ratio. The raise of stage load will inevitably result in supersonic inlet flow from root to tip of the blade. Therefore the aerodynamic design method of supersonic rotor is studied. Besides, the effects of three-dimensional flow in blade passages to the design are analyzed.Principles of choosing parameters for the through flow design and the blade profile design are acquired, by analyzing the effects of design parameters on through flow design results and comparing flow structures in different types of supersonic blade channels.On the top of principles above, a supersonic rotor is designed using the quasi three dimensional design method on the basis of the existing design platforms of laboratory. The design mass flow is 22.5kg/s, and the design total pressure ratio is 3.2. In the design process, the inlet and outlet flow parameters of rotor blades can be obtained from the through flow design as goals of blade profile designs. And the three dimensional loss distribution of rotor is extracted as the feedback quantity of through flow design to improve its accuracy. To simplify the blade profile design, the optimization method is brought in which can obtain blade profiles required through the numerical optimization. The design results show that the rotor can achieve the design goal with isentropic efficiency of 0.852. Thus the reliability of quasi three dimensional design method and optimization design method is verified.In the end, a set of Laval nozzle surfaces are designed as the preparation of supersonic plane cascade experimental. These Laval nozzles have reached the standard of military specifications according to the results of numerical simulation. Moreover, the infinite cascade is numerically simulated to prove that the experimental cascade can effectively simulate the plane cascade.