چكيده به لاتين
In industry, especially aeronautics, hydrogen fuel benefits from a high thermal value and, hence, higher thrust efficiency; stable price; reduced nitrogen oxide production in every flight stage due to lower fuel consumption; and carbon neutrality compared to hydrocarbon fuels. As a result, it is capable of satisfying the economic, social, and environmental requirements of sustainable energy development, and, therefore, it is considered a sustainable fuel for jet engines. Three research methods are used to carry out this project. In order to simulate the turbofan and extract the results, it is required to convert the thermodynamic equations governing the turbofan into MATLAB code and obtain the optimal hydrogen turbofan structure via optimization using genetic algorithm in two steps. The design parameters are required as default values for this process. The engine selected for this thesis is the General Electric GE90 turbofan engine. Hence, three research methods are used for this project, namely software writing (for the simulation), analysis or modeling (deriving the required formulas and coding them in MATLAB), and case study (selecting the GE90 engine for the project). The results obtained from this project are as follows: After optimization, the optimal values of the bypass ratio, the fan pressure ratio, and the total pressure ratio of the hydrogen turbofan were obtained to be 10.2965, 1.6111, and 39.49, respectively. Moreover, the following were obtained in the simulation for the design point (at a cruise altitude of 10668 meters) by changing the original hydrocarbon-based GE90 turbofan with a bypass ratio of 8.1 and a total pressure ratio of 40.44 to the optimized hydrogen-based GE90 turbofan with a bypass ratio of 10.2965 and a total pressure ratio of 39.49: The net thrust force increases by 16.27 percent; the thrust-specific fuel consumption decreases by 65.90 percent; the thermal efficiency increases by 2.65 percent; the propulsive efficiency remains almost unchanged with a mere reduction of 0.2 percent and provides adequate propulsive conditions; the total efficiency increases by 2.5 percent; the emission of nitrogen oxide reduces by 68.25 percent throughout the cruise phase of the flight cycle; and the fuel mass flow rate decreases by 60.29 percent. However, only by changing the fuel from hydrocarbon to hydrogen in the GE90 turbofan with a bypass ratio of 8.1, cruise altitude of 10668 meters, and Mach number of 0.83, the emission of nitrogen oxide throughout the cruise phase of the flight cycle falls by 61.90 percent. The following were obtained in the simulation for the design point (at a cruise altitude of 10668 meters) by changing the original hydrogen-based GE90 turbofan with a bypass ratio of 8.1 and a total pressure ratio of 40.44 to the optimized hydrogen-based GE90 turbofan with a bypass ratio of 10.2965 and a total pressure ratio of 39.49: The net thrust force rises by 4.53 percent; the thrust-specific fuel consumption falls by 3.7 percent; the thermal efficiency increases by 3.16 percent; the propulsive efficiency is improved by 0.7 percent; the total efficiency rises by 3.86 percent; the emission of nitrogen oxide per 1 kilogram of burnt fuel falls by 3.94 percent; the total emission of nitrogen oxide throughout the cruise phase reduces by 16.67 percent; and the fuel mass flow rate increases by 0.6 percent. Similar results were obtained for a process similar to the cruise state (design point) at sea level (off design point).
