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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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Overview of noise types generated by turbocharger compressor
Paulík, Lukáš ; Novotný, Pavel (referee) ; Vacula, Jiří (advisor)
The bachelor thesis is focused on the analysis of aerodynamic noise coming out of the compressor of turbocharger. The findings concerning the work of a radial compressor in connection with the production of the noise spectrum were overtaken from individual home and foreign publications. Main attention has been focused on the noise generated in the compressor impeller. As a basis for the generation of noise in the compressor, its characteristic and the operating line marked in it are used as a result of the cooperation of the engine with turbocharger. In individual chapters are described the sources of noise generated by, the rotation of the impeller blades, the supersonic current entering the impeller eye, the overflow of air between the blades and the compressor housing, the rotating stall and the surge of the compressor.
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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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Overview of noise types generated by turbocharger compressor
Paulík, Lukáš ; Novotný, Pavel (referee) ; Vacula, Jiří (advisor)
The bachelor thesis is focused on the analysis of aerodynamic noise coming out of the compressor of turbocharger. The findings concerning the work of a radial compressor in connection with the production of the noise spectrum were overtaken from individual home and foreign publications. Main attention has been focused on the noise generated in the compressor impeller. As a basis for the generation of noise in the compressor, its characteristic and the operating line marked in it are used as a result of the cooperation of the engine with turbocharger. In individual chapters are described the sources of noise generated by, the rotation of the impeller blades, the supersonic current entering the impeller eye, the overflow of air between the blades and the compressor housing, the rotating stall and the surge of the compressor.
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