Design Technology Of Highly Loaded Supersonic And Transonic Compressor Rotor

With the development of high thrust-weight ratio of aeroengine, it puts forward higher demand of compressor component performance. Because the compressor should realize to get higher pressure ratio with less stage, so, in order to manufacturing a compressor with high loads and high properties of cascade plays an important role to improve the properties of compressor aerodynamics. MIT completed the design works of single stage with high loads transonic compressor. It signal that it is possible to achieve the replacement of traditional fan with two signal stages , even three stages to single stage fan.The major task of this paper is to look for a design method of adsorption type compressor which can make simple control only in static cascades or rotor cascades and meet the load and efficiency. First of all, with the basic of concept of low reaction degree can applied to supersonic primitive stage, we can put forward a new method to design the transonic compressor. Just while doing the one-dimensional design, we just consider the work of supersonic blade to flow as two independent parts: the energy from the work of shock wave to flow and flow turning. And calculate the process of flow of middle accordance with relative parameters absolute parameters. Among them we can regard the change process of the relative parameters as one dimension nozzle flow. We provide the blade profile design of the flow angles of import and export, at the same time, we also determined the changes of channel area, and determined the design blade profile.Second, on the basis of design principle, we can work out a complete progress on design and analysis of blade profile. We can use piecewise function on mean camber line and thickness distribution .So we can adjust design parameters'flexibly, and get several of blade profile which we need. After combining the direct and inverse problems, we can put forward a design method that on suction side and pressure sides'thickness distribution.Last, after consider the power alone to blade height and the specific detail of blade design. We design two different rotors to do the three-dimensional numerical simulation. They respectively reach 88.78% of isentropic efficiency of rotor, and 3.27of the total pressure ratio, 88.7% of the isentropic efficiency of rotor, and 3.09 of the total pressure ratio. To the former one, the outlet absolute mach number of the tip is 1.375.The latter one is 1.2, and their outlet absolute flow angle both between 46 and 60...