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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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The use of a multi-fenestron tail rotor system on a helicopter to improve flight safety

Safety of helicopter tail rotor flights depends largely on the reliability of the tail rotor control system. Tail rotor damage and failure in many cases can lead to catastrophic consequences. Helicopters having a fenestron have certain advantages over helicopters having a conventional tail rotor in terms of safety and reliability, but failure of the fenestron can also lead to catastrophic consequences. In order to improve the safety and reliability of a helicopter that has a tail rotor to compensate the reactive torque of the main rotor, a multi-fenestron control system is proposed in this undergraduate work. Within the framework of this work, conceptual design of the helicopter with multi-fenestration system, which has features, and as a result, an algorithm for designing a helicopter with multi-fenestration system was developed. In this work, also evaluated the level of improvement of safety and reliability of the helicopter with a multi-fenestration system in comparison with the traditional scheme, calculations showed the provision of a high level of reliability for a sufficiently long operating period.

Author: Artjoms Gudkovs

Supervisor: Sergey Yunusov

Degree: Bachelor

Year: 2024

Work Language: English

Study programme: Aviation Engineering

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ADVANCEMENTS IN TAILLESS AIRCRAFT TECHNOLOGY: A COMPARATIVE ANALYSIS AND PROPOSAL FOR COMMERCIAL IMPLEMENTATION

The military has a problem in developing the most sophisticated flying wings due to the relevance of tailless aircraft in military applications and the ongoing advancements in the aviation sector. This study paper delves into the extensive history of tailless aircraft, covering everything from their inception to the most cutting-edge designs available today. To develop in control systems, especially fly-by-wire technology, tailless designs are now more practical for commercial use since they are more stable and easier to handle than they were in the past. The main goals of this research are to assess the current literature on important parts of tailless aircraft technology and provide a thorough plan for their commercial deployment.The improved splitter increases the velocity by 40 m/s, although the obtained maximum velocity distribution across the aircraft was 29.3 m/s at the rear end. As a result, the aircraft is designed with higher lift and reduced drag, allowing for smoother flight in a variety of applications.Around 53% of the lift force generated is enhanced by redesigned designs. Based on the results of the study, the aircraft with the improved design had a higher lift force and reduced drag by dividing the airflow.

Author: George Mathew

Supervisor: Adham Ahmed Awad Elsayed Elmenshawy

Degree: Bachelor

Year: 2024

Work Language: English

Study programme: Aviation Engineering

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Failure Analysis and Enhancements of Cessna-172 Nose Landing Gear Fork

Landing gear provides crucial support for aircraft while on ground. It is fastened to the main structural parts of the plane. The nose landing gear transfers all ground stresses to the aircraft structure, while the aircraft is on ground. Standard airplanes have main gears and the nose gear when taxiing on the ground the nose wheel is essential for both landing safely and guiding the plane. Main landing gear is to facilitate the safe touchdown of the aircraft. When combined, the main landing gear and the nose landing gear allow for landing smooth and jerk-free. The whole weight of the aircraft is supported by the undercarriage during taxiing and landing. Using the modelling program, a design and precise geometry of the existing Cessna 172 nose landing gear fork was created as well as for the proposed model of the nose landing gear. Comparison of four different materials for nose landing gear fork structures and evaluate the equivalent stress, strain and deflection was done. There is comparison of the nose landing gear fork structure with existing and proposed model. Compared to all the cases the titanium alloy material receives the lesser and nearer to the deformation of the steel.

Author: Jithin Thundiyil Appachen

Supervisor: Iyad Alomar

Degree: Bachelor

Year: 2024

Work Language: English

Study programme: Aviation Engineering

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