This is a study that is focused on developing an individual design methodology for a centrifugal impeller and generating a mixed flow impeller for a small turbojet engine by using this methodology. The structure of the methodology is based on the design, modeling and the optimization processes, which are operated sequentially. The design process consists of engine design and compressor design codes operated together with a commercial design code. Design of Experiment methods and an in-house Neural Network code is used for the modeling phase. The optimization is based on an in-house code which is generated based on multidirectional search algorithm. The optimization problem is constructed by using the inhouse parametric design codes of the engine and the compressor. The goal of the optimization problem is to reach an optimum design which gives the best possible combination of the thrust and the fuel consumption for a small turbojet engine. The final combination of the design parameters obtained from the optimization study are used in order to generate the final design with the commercial design code. On the last part of the thesis a comparison of the final design and a standard radial flow impeller is made in order to clarify the benefit of the study. The results have been showed that a mixed flow compressor design is superior to a standard radial flow compressor in a small turbojet application.

Game engine is a set of supporting tools and services for game development. It is a component designed for reuse in different games. Therefore it is very important for game engine to be designed properly as for any successfully used reusable component. The main objective in this research is to present flexible and easily extensible architectural solution suitable for the game engine, based on the analysis of today’s game engine context and existing software architecture design. During the analysis we reviewed different types of software architecture and its implementation methods, and defined functional requirements for game engine. As the result we have chosen data-driven architecture design as the most suitable for the engine development and created our game engine prototype. For each game engine module we have provided design solution and its implementation approach referring to chosen architecture.

Growing concerns about interruption to oil supply and oil shortages have led to escalating global oil prices. In addition, increased public acceptance of the global warming problem has prompted car manufacturers to agree to carbon emission targets in many regions including most recently, the Californian standards. Other legislating bodies are sure to follow this lead with increasingly stringent targets. As a result of these issues, spark ignition engines in their current form will need significant improvements to meet future requirements. One technically feasible option is smaller capacity downsized engines with enhanced power that could be used in the near term to reduce both carbon emissions and fuel consumption in passenger vehicles.This research focuses on exploring the performance limits of a 0.43 liter spark ignited engine and defining its operating boundaries. Limiting factors such as combustion, gas exchange and component design are investigated to determine if they restrict small engine performance. The research gives direction to the development of smaller gasoline engines and establishes the extent to which they can contribute to future powertrain fuel consumption reduction whilst maintaining engine power at European intermediate class requirements.

This thesis describes the design of four-stroke single-cylinder liquid-cooled engine with a displacement of 250 cm3 designed for Moto3 road racing motorcycle. The first chapter describes designs of existing modern engines and requirements to these engines. The next section describes the design of crank mechanism and its components. The following part describes balance shaft, timing mechanism, cylinder, cylinder head, crankcase, cooling system, lubrication system.

In this diploma thesis is elaborated design of diagnostic system for small jet engines. The aim is to describe the types of possible failures of jet engines, to determine important parameters characterizing the immediate state of engine and define methods for measurement of selected parameters. The first part is devoted to a description of selected types of small turbojet engines, followed by a summary of the most widely used diagnostic methods for assessing the health condition of the engine during operation. The next chapter contains calculation of the engine thermal cycle with characteristics of construction components. Then there is analysis of small jet engine failures with a description of their causes and possibilities of identification by diagnostic system. Thesis continues with a description of measurement methods and selection of the required sensors. Next chapter is focused on the proposed diagnostic system for condition monitoring of the engine. The last part is devoted to an excursion in laboratory for jet engine testing at the Technical University in Košice.

This thesis deals with the asynchronous engines, describes their structure, principles, properties, use, and briefly describes the design of three-phase asynchronous motor. The first section describes the most common three-phase induction motor, the emergence of the rotating magnetic field and the basic relationships. The second part deals with asynchronous motors for specific applications, their design and features. The next section is an analysis engine borrowed from the electric company ATAS Náchod, and The last section lists ways to improve the basic parameters of induction motors designed and optimized engine.

Rocket propulsion using the hybrid-propellant scheme is a technology that offers much promise in applications where high-performance liquid rocket engines are deemed too complex and solid rocket motors are considered to lack performance or safety. However, despite extensive research, there is still a lack of knowledge in the theoretical aspects of hybrid rocketry, especially in the area of fuel-oxidizer mixing and fuel regression rate. This lack of a good theoretical model makes the implementation of good, practical solutions and mature, well-functioning designs more diffcult. This disadvantages the hybrid rocket engine when compared to liquid rocket engines or solid rocket motors.In this study, a hybrid rocket engine burning polymethyl methacrylate (PMMA) with compressed air has been designed to the point of a preliminary design defnition. PMMA is a transparent material, and this has been utilized to create a transparent-chamber rocket engine where engine processes can be studied with various optical methods withoutinterrupting or disturbing the operation of the engine. The function of hybrid rocket engines, the technological solutions involved in designing working hybrid rocket engines and the constituent parts of hybrid rocket engines have been studied. The nature of the trade-offs between performance and simplicity that occur when designing a rocket engine are also studied, with a focus on maximizing simplicity, safety and minimizing expenses, while still designing an engine that fulfills basic requirements. The results include a design defnition with a preliminary user’s guide, a feasibility study, and a summary of the results of the hybrid rocket performance model that was used to determine appropriate design parameters.