Aerodynamic optimization of inlet design for high bypass ratio turbofan

Date

2024-1-22

Author

Kaplan, Yağız

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The inlet of the engine of an aircraft must allow the required amount of air pass into the engine with the minimum possible pressure losses and highest possible smoothness at a wide range of flight conditions such as climb and cruise situations. Moreover, the presence of the engine nacelle has an impact on the pressure distribution over the installation area on the aircraft. Therefore, the nacelle housing the engine core should be designed in the most optimum way against the adverse conditions that may occur. In this thesis, the inlet of a turbofan engine nacelle from literature, called the baseline geometry, is studied for optimal shape based on the pressure recovery ratio and drag coefficient values. The commercial computational fluid dynamics solver Fluent is used for flow solutions, and a Multi-Objective Genetic Algorithm (MOGA) is used for optimization. The optimization results indicate that compared to those of the baseline geometry, the pressure recovery ratio by the fan is increased by 3.97% and 3.02% at the climb and cruise conditions, respectively. Also, the drag coefficients are reduced by 11.43% and 17.32% at these conditions, respectively. The study has shown that the employed optimization approach utilizing the MOGA optimization fed by CFD solutions has proven a useful one for turbofan inlet shape design.

Subject Keywords

Nacelle optimization, Aerodynamics, Multi-objective genetic algorithm, Pressure recovery

URI

https://hdl.handle.net/11511/108500

Collections

Graduate School of Natural and Applied Sciences, Thesis