On Predicting the Flight Envelope of a Single-Spooled Turbofan Engine

• Main Authors: S. H. Hsu, 許勝雄
• Other Authors: S. M. Shiah
• Format: Others
• Language: zh-TW
• Published: 2003
• Online Access: http://ndltd.ncl.edu.tw/handle/83794113965414152362

碩士 === 國防大學中正理工學院 === 兵器系統工程研究所 === 91 === This thesis is aimed at the performance simulation and analysis of the M53-P2 single-spooled turbofan engine, with particular concern placed on its operating cycle and module characteristics at the design point condition, and the engine-based flight envelope of the Mirage 2000-5 fighter vehicle. In contents, the study begins with an extensive module analysis of the engine system, based on aerothermodynamic principles, fundamental laws of conservation, and matching rules for the engine working flow and power, to yield the governing mathematical model for solving the engine operation. Followed is the on-design performance simulation of the M53-P2, using the derived model to generate data for the engine cycle plot and the compressor map. Then is an assessment of using a twin-spool simulation model for the present single-spooled system, and a modification of the present turbofan model into a bypass turbojet. With these efforts, the final stage presents the off-design performance data of M53-P2 and the engine-based flight envelope for Mirage 2000-5, obtained by using the commercial software GasTurb. In addition to these achievements, a computer program named CSJP-4, written in Visual Basic, is also presented with validations. It shows that for the case of M53-P2 operating at its design point condition, 100% static test at sea level, all performance parameters simulated using CSJP-4 will keep an error below 4%, compared with the manufacture data. As for using the bypass turbojet model option of CSJP-4, the error is even reduced to 2%. Accordingly, the use of the present result as a basis for further studies on conceptual design, maintenance, and performance upgrade of similar engines is expectable