Collection of data, analysis and extraction of relevant information on isothermal flow characteristics, burning operation and thermos-acoustic instabilities of typical dump combustor technologies that have been in use since inception and were related to the present project. Organize, coordinate and manage the project in consultation with my supervisors, and organize the execution process of optimizing this project and to make economic decisions concerning the system implementation. Design the structure needed to perform the expected functions while sustaining its strength and withstanding excess pressure to a certain safety factor, model the system to examine its real life behavior and evaluate its validity Analyze the designed structure to show its operational, structural and functional capabilities, performance characteristic and limits. Personal Engineering Activity. To groom myself for the startup, I organized a meeting with my academic adviser and guide who gave me several innovative techniques, helped me schedule the timelines for the project and highly motivated me. I also held a meeting with the director of aerospace engineering department for postgraduate studies, who was the chief provider of all the resources that I needed in the process of executing the project. I then read widely on text books and electronic materials on flight engine technologies, mechanics of machines, fluid mechanics, solid and structural analysis and more so on computer aided design. I then reviewed several ISO standard 20 SC10- with much effort and bias on the fluid systems related codes such as ISO 16031-1:2002; ISO 19631 for aerospace fluid systems components and fittings. I then collected data from user manuals, datasheets, brochures and labels of various combustor technologies, which I sourced from the websites of the aerospace systems manufacturers. Interacting with designers, simulations and airframe engineers of these technologies, I identified weaknesses of the current technologies, frequently occurring faults, maintenance schedules and troubleshooting procedures.
407 standards codes for aircraft fuel servicing and the ISO AS/EN 9100 Series of standard codes for aerospace, aviation and defense systems, that we in-cooperated in the modeling and simulation. Data collection was a vital stage of the project, in which I analyzed several standardization organization codes for aerospace engineering technologies, including the These codes assisted me in designing the combustion process, speed optimization, ensuring low losses at suitable temperature ranges and more so made the product industrially compatible. I gathered customer specifications from the users of this product from where I made notes on some input parameters. Finally I collected data from user manuals, datasheets and databases for related fuel combustion simulations that assisted me on the parameter inputs for the model. I then drafted the functional flow diagram for the scramjet engine in different stages as in the following figure. Figure 2. Cavity Based Scramjet Combustion Engine Schematic Diagram I then designed the system step by step, by deriving the structural model for the combustion engine including the supersonic intake, the diffuser, flame stabilizer, kerosene combustor and the nozzle. From the data collected, I specified the materials for each with high strength, light weight and less sensitive to temperature changes. I then computed the chemical reaction for the mass of the kerosene required for one cycle and thus the capacity of the tank depending on the flight time and Mach 5 speed.
Some of the mathematical modeling and calculations I had to carry out in this project are as follows: Kerosene combustion equation the symbols carry their usual meanings. The system average velocities for different technologies of jets are shown in table 1. Table 1. Interrelated technologies and their respective average velocities System Average Jet velocity (M/s) Ramjet (Mach 2 at Ft) 1000 Ramjet (Mach 4 at 36000 Ft) 2000 Critical feeder gradient Where; ∆HReaction = Heat of reaction, with H as a piecewise polynomial function of adiabatic temperature of air (TAir). Where; ∏d, b, n are the pressure recovery at intake, pressure loss in combustor, pressure ratio in the nozzle and their product gives the overall pressure ratio.
PE1.2 Conceptual understanding of the mathematics, numerical analysis, statistics and computer and information sciences which underpin the engineering discipline I leveraged on my knowledge in Aerospace engineering to performed the calculations that helped me in my projects I applied the softwares relevant to aerospace to successfully implement my projects I gathered relevant information before the start of the project for me to get the basis CE1.10 CE2.9, CE3.9 CE1.14 CE2.10 CE3.12 CE1.6 CE2.6 CE3.6 PE1.3 understanding of specialist bodies of knowledge within the engineering discipline I study and prepared myself after being assigned the projects so as to be ready on what I was expected to do. I leveraged on the Aerospace engineer knowledge to guarantee the quality of my projects. CE1.5 CE2.5 CE3.5 CE1.3, CE1.7-9 CE2.3, CE2.7-9, CE3.3, CE3.7-10 PE1.4 Discernment of knowledge development and research directions within the engineering discipline I review the relevant standards and because the project was to meet international standards . I collected all the information that I wanted before the inception of the project to have the basis of implementation. CE1.6 CE2.5 CE3.5 CE1.6, CE2.6, CE3.6, PE1.5 Knowledge of contextual factors impacting the engineering discipline I embraced teamwork because I knew the benefits in terms of sharing ideas and timely delivery. Safety was big consideration in my project because I know their impacts when it comes to engineering project. I communicated in official languages CE1.16, CE2.15, CE3.16, CE1.17 CE2.16