Optimization Design Of Aerodynamic Performance For The High Pressure Compressor In Gas Turbine

As the one of the three core components of the gas turbine,the performance of the compressor has a very big impact on the overall performance.With the development of times,more stringent performance metrics are put forward so as to meet the higher requirements.Compressors with higher pressure ratio,higher efficiency and larger surge margin are the inevitable trends of the In order to increase the output power and efficiency of a conventional gas turbine,aerodynamic redesign of high-pressure compressor components has been done in this paper.Compressor efficiency and design flow has been improved,so that it can match the power of the gas turbine after modification.The optimization redesign in this paper in based on the quasi-three-dimensional aerodynamic design method,the main work is as follows,First,reassign the aerodynamic parameters of all levels and of carry out the one-dimensional flow-through design,ensuring that the basic structure of the high pressure compressor unchanged.According to the results of one-dimensional flow-through design,the meridional flow channel of compressor is been optimized designed.And the S2 stream surface design calculations have been carried out using the streamline curvature.The calculation results are be checked,after repeated cycling,preliminary scheme is carried out.Then,verifying Calculations has been done to check the number of compressor blades,axial length,leaf shapes and other geometric parameters,making ensure that the number of blades is reasonable.After that,some general loss models are used to analyze the preliminary scheme.A satisfied high-pressure compressor aerodynamic optimization scheme is got after few cycles and the leaf has been modeled three-dimensionally.At last,the design scheme and the prototype of high pressure compressor have been analyzed three-dimensionally by using numerical simulation method.The characteristic curve at the design speed of compressor is obtained by the calculation.The calculation results shows that preliminary scheme adopted in this paper makes the work efficiency of the compressor at low working condition improved by about 8%,the working flow rate also meets the requirements of the proposed design.Meanwhile,by analyzing two flow fields at different working conditions,some deficiencies have been found which points out the direction of the future work.