Scholarly Publication
Permanent URI for this collection
Browse
Recent Submissions
Now showing 1 - 5 of 23
- ItemComputational Development and Aerodynamic Analysis of a Single-Stage Launch Vehicle to Subdue Post-Launch Risk(FETiCON, 2023-06-05) Jinadu Abdulbaqi; Koloskov V.; Dmytro T.; Oluwatofunmi A. M; Olayemi A. OlalekanThe aerospace industry has prioritized reducing fatalities and failure rates after the launch of a vehicle resulting from system or engine failure. Rocketry has been difficult over the years, and international players in the industry are constantly attempting to learn from any failures. This paper aims to decrease material, resource, and payload waste while ensuring crew safety by focusing on the computational modelling and aerodynamic analysis of a single-stage launch vehicle. CATIA V5 was utilized to create the computational model of a triggered nose cone rocket booster while ANSYS was used to analyse the trigger nose cone at different angles of attack and determine how the trigger nose cone will behave in case of emergencies such as system or engine failure, which could lead to the complete explosion of the launch vehicle. Based on the current findings, the trigger nose cone is not in the safe zone when ejected at an angle of attack greater than 20° due to the shockwave's effect on its surface when ejected from the main body of the launch vehicle.
- ItemCFD Analysis of A 3-Bladed NACA 0018 Vertical Axis Wind Turbine for Deployment in Ilorin, Kwara State, Nigeria(FETiCON, 2023-06-05) Olayemi Adebayo Olalekan; Ajide Favour Tomisin; Ibitoye Emmanuel Segun; Obalalu Martins Adebowale; Jinadu Abdulbaqi; Anyaegbuna Elochukwu BenjaminDuring the last few years, vertical axis wind tubines have evolved as a suitable supplement to energy production worldwide. There has been a lot of interest in vertical axis wind turbines as a small-scale renewable power converter because they can be used in places where the wind speeds are turbulent or unsteady. When investigating the aerodynamic characteristics of vertical axis wind turbines, computational fluid dynamics has been shown to be one of the most effective methods. There is a need for better knowledge of the factors that influence the accuracy of computational fluid dynamics. The aim of this paper is to demonstrate the influence of these factors on the simulation of a low-speed turbine to guide the execution of accurate computational fluid dynamics simulations of vertical axis wind turbines at varying tip speed ratios and solidities. To simulate the turbulent, unstable fluid flow around the turbine, we used a 2D SIMPLE approach with the help of ANSYS FLUENT. In the study, it was found that when the tip speed ratio is low, the result is largely dependent on the azimuthal increment, and a fine azimuthal increment of 0.1 is usually better for low tip speed ratios
- ItemCFD Analysis of a 3-bladed NACA 0018 Vertical Axis Wind Turbine for Deployment in Ilorin, Kwara State, Nigeria.(FETiCON, 2023-06-05) Olayemi O. A.; Ajide T. F.; Obalalu A. M.; Ibitoye S. E.; Jinadu Abdulbaqi; Anyaegbun B. E.The aerospace industry has prioritized reducing fatalities and failure rates after the launch of a vehicle resulting from system or engine failure. Rocketry has been difficult over the years, and international players in the industry are constantly attempting to learn from any failures. This paper aims to decrease material, resource, and payload waste while ensuring crew safety by focusing on the computational modelling and aerodynamic analysis of a single-stage launch vehicle. CATIA V5 was utilized to create the computational model of a triggered nose cone rocket booster while ANSYS was used to analyse the trigger nose cone at different angles of attack and determine how the trigger nose cone will behave in case of emergencies such as system or engine failure, which could lead to the complete explosion of the launch vehicle. Based on the current findings, the trigger nose cone is not in the safe zone when ejected at an angle of attack greater than 20° due to the shockwave's effect on its surface when ejected from the main body of the launch vehicle.
- ItemCFD analysis of vertical axis wind turbine with modified blades for deployment in Ilorin, Kwara state, Nigeria(Al-Qadisiyah Journal for Engineering Sciences, 2024-12-16) Ajide F. Tomisin; Olayemi A. Olalekan; Jinadu Abdulbaqi; Olayemi O. David; Amoloye O. Taofiq; Oladimeji T. Leke; Bambe M. JumokeResearchers and the energy industry are currently focusing their efforts on optimizing the effectiveness of vertical-axis wind turbines (VAWT) to cut down on the reliance on energy supply from fossil fuels which releases gases that are toxic to the environment. As such, several methods have been applied, including increasing the velocity and modification of both the trailing and leading edges of the aerofoil. In the present investigation, numerical studies of the flow on the wind turbine blades with a NACA0015 airfoil section equipped with and without tubercles on the trailing edge were conducted using ANSYS Fluent. A computational domain of 2000 mm by 35000 mm was employed with the K-W SST turbulence model. This two-dimensional computational fluid dynamics (CFD) analysis was performed with Ilorin, Kwara State, Nigeria wind data that was received from the Nigeria Meteorological Agency (NIMET). The modified blade with a wavelength of 0.09m and an amplitude of 0.004m is seen to have a better thrust than the unmodified blade. It produced a thrust of 118 N for a tip-speed ratio (TSR) of 4.0 compared to 109 N of the unmodified blade at the same TSR and that of the modified blade (1) which attains 107 N. Also, its coefficient of performance is 5% and 6% higher than that of the straight and modified blades (1) respectively, These results suggest that an increase in the tubercle’s wavelength and amplitude increased the maximum thrust.
- ItemUnsteady performance of degraded compressor and turbine blades of an aero-engine at varying ambient and turbine inlet temperatures(FETiCON, 2023-08-04) I. O. Otaiku; I. O. OtaikuThe paper presents the modelling of unsteady performance of a degraded 4-stage compressor and single stage gas generator turbine blades of PT6T turboshaft aero-engine of a helicopter. The two sections were set as control volumes for analytical and numerical modeling. Numerically, The blade specimens (NACA 65 series) were developed using SOLIDWORKS 20 and simulations performed with FLUENT in ANSYS 20.0. The RANS (Reynolds-averaged Navier–Stokes) equations with Shear Stress Transport model SST (k-w) were chosen for the unsteadiness of pressure and temperature distributions over different levels of reductions in surface area of the blades’ pressure side. 900 x 103 mesh elements size were selected and the boundary conditions-inlets for the two control volumes were 295-325 K and 1083 – 1245 K for compressor and turbine respectively. Analytically, equations for different levels of degradations (surface area reductions) were developed to determine their flow performance at new pressure and temperature for compressor (∆P_2C,∆T_2C) and turbine (∆P_3T,∆T_3T) with change in time and the corresponding rise in centrifugal stress. Results from FLUENT predicts the performance of the sections for 10% surface area reduction with complex structure in the turbulent flow imposes high fatigue stress, hence shows the highest closeness to surge margin. For the compressor, the result emphasizes the impact of inlet conditions on degraded blades over exit conditions. Also in the turbine, velocity contour shows adverse/backward flow as a result of high turbulence formation and rising fatigue due to change in exit pressure flow from stage to stage in the compressor. This exit pressure determines the TIT in the turbine which is a function of efficiency of the single stage gas generator turbine and is crucial to the overall efficiency of the engine and the safety of the engine as a whole. In conclusion, the inter-component flow behaviour between the degraded compressor and turbine as revealed in this study shows the near real-life situation of the engine performance. Summarily, the accurate engine life estimation can be deduced from TIT rising from 1100-1200 K and centrifugal stress 60MN/mm2.