National Repository of Grey Literature 3 records found  Search took 0.01 seconds. 
Fourth-generation biofuels for jet engines
Marko, Adam ; Mišík, Ondrej (referee) ; Malý, Milan (advisor)
The bachelor thesis deals with the decarbonisation of air transport and the possible use of biofuels to power jet engines. As the use of the current fuel, kerosene, is time limited due to finite oil supplies, research and testing of its environmentally friendly successors is necessary. Equally important is the parallel development of compatible aviation and airport infrastructure, both in the form of airframes, engines and fuel systems and ground support equipment. In the event of a transition to a new type of aviation fuel, it is essential that it is technically advanced, affordable, environmentally sound, safe and has a wide supply chain. Currently, the scientific community is most focused on the use of sustainable aviation fuels SAF, hydrogen, ammonia, LNG and e-fuels. To qualify as a biofuel, the production process must be carbon neutral and the primary source of production must be renewable energy.
Design of hydrogen jet engine to 1kN thrust
Mikulenka, Karel ; Šnajdárek, Ladislav (referee) ; Škorpík, Jiří (advisor)
This thesis includes a brief history of jet engines using hydrogen as fuel. Calculation of thermodynamics of small engine with thrust up to 1 kN which is in modern day used in practice drones or ballistic missiles will be conducted. Given initial parameters compressor selected is of radial type. Calculation of radial compressor and its verification in EES software. Issue of combustion chambers is presented and calculation of chamber balance is carried out. Computation of turbine and blading layout. Proposal of jet for expansion into atmosphere and engine thrust. Comparison of contemporary projects researching hydrogen propulsion in aerospace with their conventional counterparts and assessing their feasibility compared to other types of renewable fuels.
Design of hydrogen jet engine to 1kN thrust
Mikulenka, Karel ; Šnajdárek, Ladislav (referee) ; Škorpík, Jiří (advisor)
This thesis includes a brief history of jet engines using hydrogen as fuel. Calculation of thermodynamics of small engine with thrust up to 1 kN which is in modern day used in practice drones or ballistic missiles will be conducted. Given initial parameters compressor selected is of radial type. Calculation of radial compressor and its verification in EES software. Issue of combustion chambers is presented and calculation of chamber balance is carried out. Computation of turbine and blading layout. Proposal of jet for expansion into atmosphere and engine thrust. Comparison of contemporary projects researching hydrogen propulsion in aerospace with their conventional counterparts and assessing their feasibility compared to other types of renewable fuels.

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