Preliminary Design And Performance Calculation For Multistage Axial Flow Compressor

Multistage axial flow compressor is one of the three core components of aero-engines,The performance of a compressor will directly affect the quality of an aero-engine and it’s always a major constrain in the design of aero-engines.Althrough 3-D numerical simulation is more and more mature,The design of Multistage axial compressor is very complicated,the theory and layer of compressor design is still clear: 1-D design offer Preliminary Design;2-D through-flow calculation offer Detail flow;3-D CFD analysis offer an assessment and optimization.In this design system,1-D Preliminary Design ad performance calculation which is uesd inparameters selecting and the determination of Preliminary Design is the first step of compressor design,so it the most important part of compressor design system.In the early 1980 s,Chinese Aircraft engine research institute introducted the 1-D Preliminary Design and performance calculation procedure from Russia.This procedure made an important role in the resaerch of aero-engines for China.However,the empiricial model of this procedure was developed from 1970s-1980 s which can not meet the requst of high loading level compressor in nowdays.So we must improve this procedure before using it.But,this procedure is very complexitied.We did not do extensive reading after it’s introduction,which will take bad effcet on modification in the future.In the situation,this thesis based on the extensive reading of this procedure,systematicly studied 1-D Preliminary Design and performance calculation.Specific study are as follows:1.Systematic study of 1-D Preliminary Design ad performance calculation;2.Made an comparison betweem the result of 1-D Preliminary Design and performance calculation and experimental data of 10 stage high pressure compressor,in the situation of default coefficients.However,there are sone difference between the result of performance calculation and experimental data.In order to reduce the difference,We adjusted these coefficients and get the value of them in different rotate speed.3.Becasue of the importance of the distribution of loading in every stage.We combine the genetic algorithm and 1-D Preliminary Design and performance calculation method.Made a study of the distribution of loading in every stage,get the optimal distribution of 4、5、6 stage compressor,in the best design point.Finally,optimized the original distribution of loading in every stage in a 6 stage compressor,increased the performance of it.