A Simulation Study on the Performance and Operating Cycle of a Twin-Spooled Turbo-Engine

• Main Author: 林豪傑
• Other Authors: S. M. Shiah
• Format: Others
• Language: zh-TW
• Online Access: http://ndltd.ncl.edu.tw/handle/40339848384818624568

碩士 === 中正理工學院 === 兵器系統工程研究所 === 88 === The purpose of this article is intended to utilize a theoretic method to simulate the steady operation cycle of twin-spool gas turbine engine under on-design specification. With the above result, the off-design performance can then be predicted. The major achievement contains analysis on characteristics of engine components, establishment of integrated model, derivation of system performance simulation, as well as development of practice simulation program. Turbofan and turboshaft engine are most common used for weapon system trajectory vehicle. And since compressor, burner and turbine are main components in operation cycle, discussion on operation theory and matching of above-mentioned components is essential for understanding of engine performance as well as application for R&D, manufacturing and maintenance evaluation. The author starts with a study on a simple twin-spool turboshaft engine to establish the foundation for research. Further research is focused on simulation and analysis on performance of a mixed type twin-spool turbofan engine. Characteristic equations derivated from fundamental thermodynamic theory for each component is utilized to establish mathematic governing model, with which a set of equations is obtained with constraint condition of conservation of mass and energy and matching of shaft power. Finally a program using Excel and VBA is developed for solution to calculate the overall performance. To validate the mathematic model, performance is calculated using the software program on T53-L-13B and a typical 6000 pound rated mixing turbofan engine. The result shows a fairly good matching in physical trending when compared with output calculated from GasTurb developed by Kurzke in 1997.