Optimization Design of Aspect Ratio and Solidity of a Heavy-Duty Gas Turbine Transonic Compressor Rotor
Author:
Liu Shuaipeng,Geng Shaojuan,Li Xinlong,Jin Yun,Zhang Hongwu
Abstract
To investigate the influence of blade aspect ratio and solidity on the performance of heavy-duty gas turbine transonic compressors, a multi-objective optimization design platform was built by adopting the blade parameterization method based on the superposition of thickness distribution on the suction surface, the Kriging surrogate model, and the NSGA-II optimization method. The spanwise distribution of solidity and number of blades were the optimization variables. The multi-objective optimization was carried out with isentropic efficiency and stall margin as the objective parameters for the inlet stage transonic rotor of an F-class heavy-duty gas turbine compressor. The results show that the isentropic efficiency and stall margin at design condition with a constant mass flow rate can be improved by 0.96% and 18.7%, respectively, and the total pressure ratio can also increase. The analysis shows that, for regions where the shock wave–boundary layer interaction is obvious, increasing the solidity can reduce the shock wave loss, the shock wave–boundary layer interaction loss, and the end wall loss, and reducing the aspect ratio can reduce the blade boundary layer loss. The spanwise distributions of solidity and aspect ratio determine the stall margin by affecting the radial matching of the load of each blade section. Tip solidity near the tip region needs to be determined according to the pressure field established by the bulk of the flow.
Funder
National Science and Technology Major Project of China
Subject
Electrical and Electronic Engineering,Industrial and Manufacturing Engineering,Control and Optimization,Mechanical Engineering,Computer Science (miscellaneous),Control and Systems Engineering
Reference24 articles.
1. Three-Dimensional Flowfields Inside a Transonic Compressor with Swept Blades;Hah;J. Turbomach.,1991
2. Lieblein, S., Schwenk, F.C., and Broderick, R.L. (1953). Diffusion Factor for Estimating Losses and Limiting Blade Loadings in Axial-Flow-Compressor Blade Elements.
3. Development of Fan/Compressor Techniques and Suggestions on Further Researches;Chen;J. Aerosp. Power,2002
4. Obrecht, T. (2013). HP Compressor Preliminary Design, von Karman Institute for Fluid Dynamics.
5. Axial Compressor Aerodesign Evolution at General Electric;Smith;J. Turbomach.,2002
Cited by
2 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献