Research On The Three-dimensional Inverse Method For Compressor Blade Design

The compressor blade design methods can be divided into direct method(mainly refers to theanalysis and design method)and inverse method.In direct method(mainly refers to the analysis anddesign method)always takes a lot of time and cost,and the results strongly depend on experience andtheory of knowledge of the designer,and the possibility of achieving innovative program is small;Inthe inverse method,the designer give some aerodynamic parameters in the flowfield based on thedesign requirements,then use these aerodynamic parametesr as the input information of inversedesign,then obtain the blade profile directly through relationship between aerodynamic parametersand physical characteristics. Therefore, the advantage of inverse method is it designing efficient,andless dependent on the designer’s experience,can shorten the design cycle, especially remarkable in thethree-dimensional blade design.This paper based on the efficient inviscid inverse design method of-D compressor bladedeveloped by A. Demeulenaere and Van den Braembussche from Von Karmen Institute,combinedwith the study of inverse design method of2-D made by our group, carried out some study ofinviscid inverse design method of3-D compressor blade including centrifugall compressorblade.The main research work and achievements of this pa3per includes:1.Construct the process of threed-dimensional inviscid inverse design metho,carry out sometheoretical analysis of “permeable wall” and three dimensional profile modification method,providethe theoretical basis of three-dimensional inviscid inverse design method.2.Based on the self-developed3-D viscous flow calculation program NAPA, on the basis of itsEuler solver,achieve the three dimensional inviscid inverse design method under the absolutecoordinate system.And do some test and verify on the effectiveness of the example of subsonic axialflow compressor made by three dimensional inviscid inverse design method of this paper.3. Aiming at calculating the inverse problem flowfield in the rotor coordinate, the permeableboundary in rotor coordinate is analysed in theory and the algorithm is changed. The capacity ofcalculating the inverse flowfield and modifying the3-D blade quickly and accurately is verified in thecase of subsonic axial compressure blade.4.Improve the permeable boundary due to the large deviation between target pressure and initialpressure,and it is verified in the example of eliminating the axial flow compressor rotor blade channelshockwave. 5. The generality of the three-dimensional inviscid inverse design method used in the conditionof strong three-dimensional flow is verified in the case of designing the Krain centrifugalcompressor by inverse method. give the reasons of large deviation occuring in the shroud section andconstruct two examples to analyse the correctness of large deviation. Thus the direction of improvingthe three-dimensional blade modification method is shown, and provide the necessary foundation inthis paper.