Optimized Aerodynamic Design Of Multi-stage Axial Compressor Based On DoE

At present, in order to meet the needs of modern aeroengine high thrust-weightratio and low cost, domestic and foreign military or civil aviation engine compressordevelops rapidly, mainly mainfested in the stage load increased significantly. Theconventional aeroengine compressor aerodynamic design method based on empiricalmode due to the huge limitations have been unable to meet the new generation aviationpower needs, with a new design method and technique has become inevitable. DoEexperimental design is a classic design optimization method; its uniquemulti-dimensional array algorithm can effectively solve the initial design ofmultivariable, compressor large range of characteristics, to solve the problems ofconventional design experience of great significance.The paper introduces a space-iflling design and response surface optimizationdesign mathematical model and application. Detailing the course of development of thedomestic and international air axial flow compressor design methods based onhighlighting the quasi three-dimensional aerodynamic design. In a detailed analysis offoundation, pointed out that the current flow path design of quasi3D necessity andlimitations, and completed the DoE experimental design method is introduced into thecompressor preliminary design theory the feasibility and practical operation analysis.Specific design scheme design of preliminery flow surface and detail post-optimization analysis of two phases. In the initial design phase of flow surface,according to the requirements of the overall design selection of engine flow and mainstage parameters, and then a given compressor geometry size, diffusion factor, loadcoeiffcient adjustable parameters of variable range, in the optimal eiffciency principleby DoE experiment design method, separately for each discrete point using onedimensional inverse problem method, selection of optimal solution and efficiency.Based on the results of analysis show that the proposed DoE based pneumaticoptimization scheme can maintain the original eiffciency and greatly improve thecompressor single stage pressure ratio and total pressure ratio, also can greatly reducethe number of compressor stages and shortening the compressor axial length. In the post-optimization and analysis phase, the final design of the program designstage, along the blade from the blade root to tip to select the five computing station, theuse of quasi-three-dimensional aerodynamic calculation methods based on the axis ofsymmetry assumptions compressor conditions within the computational analysistheoverall operating characteristics of the compressor, the compressor conditions analysisshows that this design has a broader range of stable operation, completely superior tothe conventional compressor Finally, the compressor inlet total pressure and the firststage stator pre-rotation angle, response surface optimization of the design, optimizedcompressor overall performance has improved greatly than before.Later research may focus on the blade cascade selection and blade stacking methodoptimization, in order to further reduce the loss, improve the eiffciency of compressorIndicated through research, the experimental design method for compressor initialdesign and the later optimization is feasible, for China’s future development to providereference for aeroengines compressor design of high performance.