Parametric analysis of expendable type single-spool turbojet engine with a short afterburner

Abstract

A parametric, on-design performance analysis of an existing single-spool expendable turbojet engine with a short afterburner is presented in this paper. A design point mathematical model of the engine is developed to obtain the optimum system performance conditions and is implemented in a FORTRAN code. This model utilizes the engine design parameters, such as operating flight conditions, compressor pressure ratio, turbine inlet temperature, and afterburner exit temperature to predict the engine performance parameters, such as specific thrust and specific fuel consumption. Based on the same flight conditions and engine design parameters, an analysis is done by using commercial software, GasTurb, used for the performance analysis of gas turbine engines. The results obtained from the developed design point code are in a good agreement with the GasTurb and the available experimental data. Subsequently, the effects of adding a short afterburner on the performance of the engine are studied using a parametric analysis. A theoretical database for different performance parameters is obtained as a design reference for the future work.