01.1 - Aircraft Design and Integrated Systems (Theory, Methods and Tools)
A HYBRID 0D–2D WHOLE-ENGINE MATCHING FRAMEWORK FOR TURBOJET ENGINE PERFORMANCE SIMULATION
T.X.Q. Hoang¹, T.A. Pham¹, X.H. Vu¹, H.H. Nguyen¹, C.A. Pham¹, D.L. Chu¹; ¹Viettel Aerospace Institute, Vietnam
Accurate whole-engine matching is essential for reliable performance prediction of turbojet engines at the early design stage. This paper presents a hybrid 0D-2D whole-engine matching framework that balances computational efficiency and physical fidelity. Two-dimensional through-flow models are employed for the compressor and turbine, while the inlet, combustor, and nozzle are represented using simplified zero-dimensional performance models. To robustly determine the matched operating point, a hybrid global-local optimization strategy is adopted, combining Monte Carlo sampling for global exploration with the Nelder-Mead algorithm for local refinement. The proposed method is validated against experimental data under both static and flight conditions. The results demonstrate good agreement across key performance parameters, with differences remaining within 5%. These findings indicate that the proposed framework provides an effective and reliable tool for preliminary turbojet engine performance analysis and early-stage design applications.