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.