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Optimization of Turbofan Engine Performance through Blade Profile Modification

This thesis reports detailed research performed to optimize the geometries of blade rows in turbofan engines through analysis with computational fluid dynamics. The study was conducted systematically by employing theoretical analysis, along with numerical computation used to evaluate the aerodynamic performance of two different blade types. The methodology consisted of the design of blade geometries in SolidWorks, mesh generation using structured and unstructured elements, and CFD simulations on ANSYS Fluent with a focus on cascade analysis. The study commenced with the development of two designs below: Blade Design 1 having a height of 1300 mm, chord length of 294 mm at the base, and 700 mm at a height of 750 mm; Blade Design 2 at a similar height, differing only in leading edge diameters and chord lengths at different cross-sections. This enables detailed meshing such that near-wall regions and critical flow features are resolved with adequate resolution. Using a pressure-based solver, the CFD simulation was performed using the k-ω SST turbulence model, which is proper for capturing near-wall effects and handling adverse pressure gradients. Inlet velocities were considered between 1 and 40 m/s, thus analyzing performance under different operating conditions.

Author: Ajiksun Kumaradhas

Supervisor: Adham Ahmed Awad Elsayed Elmenshawy

Degree: Bachelor

Year: 2024

Work Language: English

Study programme: Aviation Engineering

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Implementation of Variable Pitch Angle Fan Blades on Gas Turbine Engine

This diploma thesis explores methods to enhance the efficiency of gas turbine engines with a focus on high bypass ratio engines. The study is structured around three objectives: (1) reviewing the principles, and advancements of gas turbine engines, (2) analyzing the design features and challenges of high bypass ratio engines, and (3) developing a variable pitch angle fan mechanism to optimize performance.The analysis of high bypass ratio engines details and their advantages, while addressing challenges in thermal management and cooling. The study successfully proposes a conceptual design for a variable pitch angle fan, demonstrating its potential to adapt to varying flight conditions and enhance overall engine efficiency.The findings suggest integrate innovative cooling, sealing technologies, and advanced control systems can significantly improve performance. The proposed variable pitch angle fan mechanism shows promising results in optimizing engine efficiency. This thesis concludes that the implementation of these advancements can achieve a notable increase in gas turbine engine efficiency, contributing to the advancement of aviation technology. Future research should continue to refine these solutions and explore additional methods to enhance engine performance.

Author: Andrejs Kazanli

Supervisor: Aleksandrs Medvedevs

Degree: Bachelor

Year: 2024

Work Language: English

Study programme: Aviation Engineering

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