Aerodynamic Performance Analysis Of Centrifugal Compressor And Retrofit Optimization Of Splitter Blade

Centrifugal compressors are widely used in the design and development of micro gas turbines because of their compact structure,small size,light weight,high single-stage pressure ratio,simple manufacturing process,and no special anti-surge regulation system.The machine acts as the main booster.With the continuous advancement of technology,the demand for high-performance centrifugal compressors is increasing.To further improve the performance of centrifugal compressors,it is first necessary to systematically study the internal flow field of the compressor and related optimization and modification techniques.In this paper,the compressor model is established according to the blade-related parameters,and the computational fluid dynamics software is used to calculate the three-dimensional numerical simulation of the impeller part of a micro gas turbine centrifugal compressor.The flow field characteristics of the centrifugal compressor are analyzed comprehensively and deeply.The main optimization of the splitter blade and the corresponding conclusions.The main research work of this paper is as follows:1.According to the data,the working principle and main structure of the centrifugal compressor are introduced in detail,the theoretical research results of domestic and foreign scholars are summarized,the relevant research progress of the internal flow field characteristics of the centrifugal compressor is described,and the related schemes for the optimization and modification of the centrifugal compressor are summarized..2.For the centrifugal compressor to be studied in this paper,the UG software is used to establish the three-dimensional model.A single flow channel model is extracted as the research object and meshed,and then the boundary conditions are set and solved by ANSYS-CFX.The accuracy of the numerical simulation was verified by comparing the test parameters in the literature.3.The internal flow field of the original airfoil of the centrifugal compressor is analyzed,and the formation mechanism and development trend of the secondary flow and wake flow structure of the internal flow field are obtained,which provides a basis for further optimization and modification.4.Analyze the influence of different tip clearances on the performance of the centrifugal compressor and the internal flow field,and design three uniform gaps at the rated speed.The performance changes of the compressor under different clearances were studied,and the internal flow field was analyzed.5.Optimize and renovate the splitter blades,mainly adjust the parameters such as the circumferential arrangement position of the splitter blades,the blade length of the splitter blades and the installation angle of the splitter blades,and compare with the original models to further optimize the internal flow field of the compressor.And draw the corresponding conclusions.