Design And Research Of Compressor Blade Pre-deformation

The structural performance of gas turbine compressor blades will directly affect the performance,reliability and economy of the whole machine.It is important to analyze the load and deformation of blades in the working condition for the design of blades,the debugging of machine performance and the prediction of stability.The application of the design technology of the blade predeformation is to match the working state of the designed blade and the working state of the turbomachinery,in order to meet the design requirements of the performance of the parts and the whole machine.In this paper,a marine gas turbine compressor with a zero stage blade and an aero turbofan fan blade is taken as the object,and combined with the practical application of ANSYS commercial software,the numerical simulation of multi physical field coupling is carried out for the strength analysis and pre deformation process of the long blade.The paper is mainly aimed at the deformation of the cold / hot blade.The process was analyzed to explore the cold / hot state of various parameters and laws of long blades.Specifically,the following work has been carried out mainly:(1)The flow and solid coupling method in time domain is used to simulate the three-dimensional numerical simulation of the fan blade model of a compressor blade and a large culvert ratio turbofan engine respectively.The dynamic equations are solved by the discretization of the continuous regions of the solid and fluid fields and the construction of interpolation functions,and the physical letters are realized on the interface of the fluid solid coupling.The flow field simulation and load extraction under the combined action of aerodynamic force and centrifugal force are analyzed,and the relationship between the strength and deformation of the blade under load and the material property parameters,working conditions and geometric characteristics of the material used in the blade is also analyzed.(2)On the basis of the data of stress and deformation produced by two kinds of blades under the combined action of centrifugal aerodynamic load,the cold / hot leaf shape of the blade is corrected respectively to two kinds of blades.The results show that during the pre deformation design of the blade,the variation of the total amount of deformation in the pre deformation of the compressor blade and the fan blade of the compressor is approximately the same.The first 8 times,especially in the first 5 iterations,the change of the convergent residual is obvious,the correction of the deformation amount is more intuitionistic,and the difference of the deformation amount after the 12 th iteration.The change has been close to the standard of convergence.The iteration after the beginning of this time has been inclined to the nonlinear variation law.When the maximum residual difference of the whole blade satisfies the convergence condition,it is considered to be completely convergent,and the cold state blade is the preformed blade model.Finally,the optimization of the blade pre-deformation under the blade multiple section geometric feature angle method is introduced and studied in this article.The multiple blade sections of the theoretical design blade are chosen and the spatial displacement variable is converted to several geometric angle parameters that including installation angle,geometric inlet angle and geometric exit angle of every blade section.On the basis of these geometric angle parameters,the final artifactitious cold blades and the pre-deformation hot blade can be obtained after the repeated iteration.The effectiveness of this method is verified through numerical simulation analysis.