Simulation of Complete Dual Compressor Turbojet Engine with Combustion

Anotace: This article presents a comprehensive study on the simulation of a complete dual compressor turbojet engine with combustion. The engine model consists of a single-stage axial compressor, a single-stage radial compressor, a combustion chamber, and a single-stage axial turbine. The simulation of the complete engine allows for the consolidation of boundary conditions and input parameters, resulting in more accurate information transfer between different segments. The study contributes to advancements in engine design, performance optimization, and the broader understanding of similar propulsion systems. The methodology, boundary conditions, challenges faced, and results obtained from the simulations are discussed in detail. The successful creation of the model demonstrates its potential for optimizing engine components and studying their behavior under various flight conditions.