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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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Methodology of temperature measurement behind jet engine
Koutný, Martin ; Koštial, Rostislav (referee) ; Matějů, Jiří (advisor)
This thesis is focused on temperature measurement behind jet engine. The theoretical part introduces chosen ways of temperature measurement. The practical part is divided into design (and later assembly) of the measuring stand, methodology of measurement and the measurement itself. The main outcome are heat maps gained by measuring temperatures behind TJ – 42 jet engine.
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Design VUT 022 Aircraft with Jet Engine according to CS-22 Regulation
Matěják, Vladimír ; Popela, Robert (referee) ; Juračka, Jaroslav (advisor)
The diploma thesis deals with the design, load calculation and stress analysis of a composite wing construction of an airplane based on the construction of the airplane VUT 001 Marabu in order to fulfil conditions of CS-22 specifications. As a part of the thesis are basic mass, moment and aerodynamic characteristic of the airplane analyzed. Also the modification of the center part of the fuselage is designed in order to enable a jet engine instalation inside the construction.
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Modern low-emission combustion chamber for jet engines
Mašek, Jakub ; Nastálek, Ondřej (referee) ; Šplíchal, Miroslav (advisor)
Bachelor´s thesis examines modern low-emission combustion chambers for jet engines. It´s foremost aim is to specify construction parameters of low-emission combustion chambers, compare it´s features and comprise the use of these combustors in civil aviation. Thesis deals with reasons of modern low-emission combustion chamber development and estimate future development in the region of aircraft industry. Another aim is to specify legislations of aviation emissions, history of certification standards and organizations, which make and control these limits.
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Fuel control unit system of jet turbine engines
Mašková, Šárka ; Bencalík, Karol (referee) ; Šplíchal, Miroslav (advisor)
This bachelor thesis describes fuel control unit systems of jet turbine engines, specifically historical development of these systems including current research, operating processes of different types of fuel control unit systems and important controling quantities. The last part of the thesis describes fuel control unit system produced by Jihostroj a.s. company for M601 engine.
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Engine simulator - HW development
Starosta, Michal ; Hutyra, Tomáš (referee) ; Klusáček, Stanislav (advisor)
STAROSTA, Michal . ENGINE SIMULATOR – HARDWARE SUGGESTION. Bachelor’s thesis. Brno: University of Technology, Faculty of electrical engineering and communication, 2009. 51 s., Supervisor.: Ing. Stanislav Klusáček. This work describes suggestion of concept of simulator of jet egine for purposes of testing control unit for this engine FADEC. There are described possibilities of software and hardware facilities for simulator realization. Possibilities of software facilities are mainly focused on Matlab / Simulink program to communicate in real time with card for data acquisition.
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Design of coaxial high-speed gear reducer
Neklapil, Libor ; Ing. Tomáš Hubáček, Ph.D (referee) ; Bradáč, František (advisor)
The thesis deal with design of coaxial high-speed gear box for small-scale turboshaft engines. At the beginning a study of problems was performed and for design concept was elected version of single-shaft turbo-engine with electric generator. Kinematic diagram, type of gear design, material and lubrication method was designed. Further was solved proposal of basic gearing parameters, choice of the number of tooth and basic proposal calculations were performed. Was performed check calculation of gearing, calculation of bearings durability and was processed design documentation in required range. Designed gear reducer has two stage with three coutershafts, that are deployed evenly about main axis of reducer. First stage is gear with external gearing, second stage with internal gearing. The thesis may be used as a template for next similar gear reducers design.
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