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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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Drone manipulator optimization and integration in affordable quadcopter

This paper explores the development of a drone-attachable manipulator designed to perform construction and maintenance tasks, moving beyond the traditional use of UAVs for monitoring. Our primary objective is to design a manipulator capable of lifting objects weighing up to 300 grams, adhering to principles of low cost, ease of manufacturing, and high quality. We begin with a literature review of UAV types and their suitability for integration with manipulators. The design process involves creating multiple manipulator prototypes using Solidworks for simulations to gather data on performance and structural integrity.Static stress and displacement analyses are conducted to identify areas of high stress and potential deformation. Initial designs demonstrate that the static force required to hold a 300-gram object exceeds the capabilities of our prototypes. The final manipulator design is tested for its lifting capabilities and operational limitations. Re The study concludes with an evaluation of the design process, limitations, and potential for future applications of UAV-integrated manipulators in infrastructure construction and maintenance

Author: Arvis Maiželis

Supervisor: Adham Ahmed Awad Elsayed Elmenshawy

Degree: Bachelor

Year: 2024

Work Language: English

Study programme: Aviation Engineering

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Development of an Alternative Mean of Compliance for inspecting passenger door stops on Embraer ERJ - 145 using Fluorescent penetrant Non-destructive Testing method.

This bachelor thesis focused on Development of an Alternative Mean of Compliance (AltMoC) for Inspecting the passenger door stops from Embraer ERJ - 145 aircraft Using Non-Destructive Testing Fluorescent penetrant method. The main goal of this work is to simplify the task with the help of a developed inspection for checking a structural component. A structural component is subject to fatigue and physical stress on it, as well as corrosion. Detailed detection of the smallest damage and metal fatigue. The developed AltMoC is aimed at significantly accelerating work processes, making inspection cheaper as well as having a simplified and clear process using penetrant testing. Having carried out research, the Author, carefully select the appropriate method for inspecting a structural component based on the type of material from which it is made, considering its’ its physical and chemical properties. Develop the correct sequence of actions in the instructions. Thanks to this, the workflow time and the risk of errors occurred due to Employees' misunderstanding significantly reduced.

Author: Deniss Zaharovs

Supervisor: Iyad Alomar

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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