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Entransy analyses of the thermodynamic cycle in a turbojet engine

Science China(Technological Sciences) 2017年第8期60卷 1160-1167页

作者： CHENG XueTao LIANG XinGang Key Laboratory for Thermal Science and Power engineering of Ministry of Education School of Aerospace Tsinghua University Beijing 100084 China The Administrative Committee of the Modern Industrial Park New District of Zhengpu Port Maanshan 238261 China

The analysis and the design of turbojet engines are of great importance to the improvement of the system *** researchers focus on these topics,and many important and interesting results have been *** this paper,the thermodynamic cycle in a turbojet engine is analyzed with the entransy theory and the T-Q *** ideal thermodynamic cycle in which there is no inner irreversibility is analyzed,as well as the influences from some inner irreversible factors,such as the heat transfer process,the change of the component of the working fluid and the viscosity of the working *** the discussed cases,it is shown that larger entransy loss rate always results in larger output power,while smaller entropy generation rate does not *** corresponding T-Q diagrams are also presented,with which the change tendencies of the entransy loss rate and the output power can be shown very *** is shown that the entransy theory is applicable for analyzing the inner irreversible thermodynamic cycles discussed in this *** with the concept of entropy generation,the concept of entransy loss and the corresponding T-Q diagram are more suitable for describing the change of the output power of the analyzed turbojet engine no matter if the inner irreversible factors are considered.

关键词： turbojet engine entransy analyses T-Q diagram inner irreversible cycle

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Numerical Simulation and Performance Analysis on Windmill Starting Process of Small turbojet engine

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Defence Technology（防务技术） 2011年第3期7卷 145-152页

作者：杨欣毅田宇朱旭程周源李冠军 Naval Aeronautical and Astronautical University Detachment 92 Unit No.92941 Naval East China Sea Fleet 19 division

A new simulation strategy is proposed for the starting process of missile turbojet engine windmill. The starting process of windmill before ignition is simulated using a radial basis function neural network (RBFNN) , and the acceleration process after ignition which model is a set of nonlinear equations is solved using a particle swarm optimization (PSO) algorithm. The introduction of PSO helped to tackle the problem of divergence caused by traditional iteration methods. The calculated result is in a great agreement with test data, which shows that the presented model has a high accuracy. The starting processes are simulated at different ignition times, and the results are analyzed synthetically. The analysis shows how the ignition time affects the starting performance of engine windmill. The method offers a useful tool for ignition time optimization as well as engine starting performance analysis.

关键词： missile propulsion turbojet engine windmill moving least squares particle swarm optimization

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