Analysis And Research On Reynolds Number Sen-sitivity Of Axial Flow Compressor

Power has always been one of the main research modules in the field of shipbuilding,and it is the foundation of the high-speed development of the shipbuilding industry.As one of the core components of the gas turbine,the performance of the axial flow compressor is related to many factors.Analyzing and optimizing the performance indicators of the compressor is of vital importance to the overall performance of the gas turbine.The change in the Reynolds number caused by the variation of parameters such as inlet temperature and pressure due to the temperature difference in the marine environment and the model test has a direct impact on the aerodynamic performance of the compressor.Therefore,research on the sensitivity of compressor blades to the Reynolds number has important theoretical and practical engineering application value.Firstly,at the one-dimensional design level,research was conducted on the influence of Reynolds number on the loss model and the deviation angle model of the compressor.Based on numerical simulation methods,a sample library of blade cascades was constructed,and mathematical modeling methods such as adaptive simulated annealing algorithm,least squares method,and multivariate nonlinear regression analysis were used to modify the traditional empirical loss and deviation angle models.Correction formulas and coefficients related to Reynolds number and maximum relative thickness distribution were given.The root mean square errors of the zero attack angle loss model and the off-design working condition loss model were reduced by 78.95% and 62.18%,respectively.The root mean square errors of the zero incidence angle deviation angle model and the off-design working condition deviation angle model were reduced by 7.23% and 54.69%,respectively.Secondly,a performance optimization design was conducted on the blade profile parameters of the midspan of the low-pressure compressor of a marine gas turbine engine,aiming to reduce the sensitivity of the blade to Reynolds number using multi-objective optimization algorithms.Numerical simulation methods were used to analyze the effect of inlet total temperature variation on the performance of the blade under variable incidence angles.The results showed that the blade with smaller maximum relative deflection in its design parameters had lower sensitivity to Reynolds number under inlet Reynolds number variation due to changes in inlet total temperature,and the optimal flow range under variable incidence angles was wider.Based on the analysis of parameter distribution for optimized blade profiles,blade tuning was performed on the first 1.5 stages of the high-pressure compressor of a certain type of gas turbine engine,including both the moving blades and the stationary blades.This resulted in reduced sensitivity to Reynolds number and increased stage efficiency 0.55% under standard operating conditions and 0.4% under ground test conditions.The findings of this study can provide reference for performance adjustments of axial flow compressors and design of highload compressors.