This study has investigated the severe corrosion of Biogas engines by the blowby gases. The formation of blowby its composition and flow rate have been measured and simulated. The nature of the piston ring sealing, lubrication and breakdown has been examined. A study of Biogas engines showed that Copper corrosion of the small end and camshaft bearings by HZS gas was the reason for engine failure. H2S is present in all Biogas at a concentration of usually less than 1%, but succeeds in chemical attack despite its good combustion properties, and the expected reaction with the bases present in the lubrication oil. The HZS was corroding in its gaseous state, but only those bearings with indirect lubrication. The solution to this problem is either to adopt force fed lubrication of the bearings, or to replace the alloy with Aluminium-Tin. The experimental work used four engines of differing wear. The constant speed work showed that the fuel content of blowby gas increases with load despite any increase in fuelling rate. This trend was consistent for all gaseous fuels present including H2S. A series of computer calculations of piston ring blowby were completed, using conventional and novel input data. The resultant blowby flow was within an order of magnitude, confirming that two blowby mechanisms, ring gap blowby and ring seal breakdown, are present on worn engines. The composition results showed that the fuel content of blowby is subject to the complex nature of the quenching process in the combustion chamber. A study of the oil present at the top ring showed that the oil is greatly modified when compared with the sump oil, as a result of thermal degradation and base depletion. The oil has a high acid TAN, which suggests it could encourage corrosive wear of the cylinder liner.

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The chapters subsequent to the design discussion describe the evolution of the project. During the progression of the project, four case studies were undertaken. Each of these case studies involved the design of an engine, using the principles expounded in the early chapters. The parts of three of these were manufactured. The project has culminated in case study four which consisted of the conception, design and component manufacture of a new type of engine: the Hudson 5 Cycle Rotary Engine. It does not reciprocate, nor is it orbital (Sarich) and is not peritrocoidal (Mazda). It operates with pure rotary motion. It also promises to have a favourable environmental aspect due to its excellent fuel efficiency and because of its exceptional power to weight and power to size ratios plus a low component count. The small size and low number of parts make it very economical to produce, both in materials and energy.

Serpentine ducts used by both military and commercial aircraft can generate significant flow angularity (inlet swirl) and total pressure distortion at the engine face. The impact of inlet swirl on the engine performance and operability must be quantified to ensure safe operation of the aircraft and propulsion system and to define installed deficiencies. Testing is performed over a wide range of flight conditions in the propulsion system flight envelope in order to quantify these effects. Turbine engine compressor models are based on experimental data which can be collected at a limited number of discrete operating points. These models can be used as an analysis tool to optimize the engine test plan and help during validation of the design. The Dynamic Turbine Engine Compressor Code (DYNTECC) utilizes parallel compressor theory and quasi-one-dimensional Euler equations to determine compressor performance. In its standard form, DYNTECC uses user-supplied characteristic stage maps in order to calculate stage forces and shaft work for use in the momentum and energy equations. These maps are typically developed using experimental data. These maps can also be created using characteristic codes such as the 1-D Mean Line Code or the 2-D Streamline Curvature Code. The 1-D Mean Line Code was originally created to predict the performance of individual compressor stages and requires greatly reduced computational time when compared to 2-D and 3-D models. This thesis documents work done to incorporate the 1-D Mean Line code into DYNTECC as a subroutine. The combine DYNTECC/1-D Mean Line Code was then used to analyze the effects of inlet swirl on the fan performance and operability of the Honeywell F109 turbofan engine. The code was calibrated and validated using the F109 cycle deck. Additional code validation was performed using experimental data gathered at the United States Air Force Academy. F109 fan maps were developed for various cases of inlet swirl and results were presented showing shifts in corrected mass flow, fan pressure ratio and fan stability limit.

The second law analysis is a powerful tool for assessing the performance of engines and has been employed for few decades now. Turbocharged diesel engines have been explored in much detail with the help of second law analyses. There is also a need to examine the turbocharged spark-ignition engines in greater detail using second law analyses as they are gaining popularity in high performance and conventional automobiles as well. A thermodynamic simulation was developed in order to investigate the effects of turbocharging on spark-ignition engines from second law perspective. The exergy values associated with the components of the turbocharger along with the engine components were quantified as a percentage of fuel exergy. The exergy balance values indicated that turbocharger does not add considerably to the overall irreversibilities and combustion irreversibility is still the major source of exergy destruction. A comprehensive parametric investigation was also performed to investigate the effects of compression ratio, intercooler effectiveness, etc. for the turbocharged spark-ignition engine over the entire load and speed range. The simulation studies helped in understanding the behavior of turbocharged sparkignition engine with these parameters. A simulation study was also performed to compare the turbocharged engine with the naturally aspirated spark-ignition engine. This study examined the engines for operating parameters like bmep and bsfc over the entire speed range and revealed that turbocharging offers higher bmep and lower bsfc values for most of the operating range. In an additional study, these engines were analyzed for the brake thermal efficiency values at part load. The results indicated that turbocharging offers marginally higher brake thermal efficiency at part loads.

A 3D graphics system usually consists of two major subsystems: geometry subsystem and rendering subsystem. The geometry subsystem performs transformation, lighting, backface culling, and clipping. The clipping is to remove the part of a triangle that is outside of the view volume by calculating the intersections of the triangle edges with view planes. The clipping operation turns out to be a time-consuming procedure in the geometry subsystem. In this thesis, we present several clipping algorithms and their hardware implementations, and compare the performance in the geometry subsystem. Furthermore, a new pre-clipping algorithm is also proposed to reduce the number of triangles that need to go through the clipping operations in order to reduce the burden of clipping operations in the whole geometry subsystem. The whole geometry system including the pre-clipping and clipping hardware is verified in a complete 3G graphics system in the Versatile FPGA demonstration board.

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Increasing energy demands and environmental problems require innovative systems for electrical and thermal energy production. In this scenario, the development of small scale energy systems has become an interesting alternative to the conventional large scale centralized plants. Among these alternatives, small scale combined heat and power (CHP) plants based on Stirling Engines (SE) have attracted the interest among research and industry due to the potential advantages that offers. These include low maintenance, low noise during operation, a theoretically high electrical efficiency, and principally the fuel flexibility that the system offers. However, actual engine performances present very low electrical efficiencies and consequently few successful prototypes reached commercial maturity at elevated costs.Considering this situation, this thesis presents a numerical thermodynamic study for micro scale CHP-SE systems. The study is divided in two parts: The first part covers the engine analysis; and the second part studies the thermodynamic performance of the overall CHP-SE system. For the engine analysis a detailed thermodynamic model suitable for the simulation of different engine configurations was developed. The model capability to predict the engine performance was validated with experimental data obtained from two different engines: The GPU-3 Stirling engine studied by Lewis Research Centre; and the Genoa engine studied on the experimental rig built at the Energy Department at the Royal Institute of Technology (KTH). The second part of the research complemented the study with the analysis of the overall CHP-SE system. This included numerical simulations of the different CHP components and the sensitivity analysis for selected design parameters.The complete study permitted to assess the different operational and design configurations for the engine and the CHP components. These improvements could be implemented for test field evaluations and thus foster the development of more efficient SE-CHP systems. In addition, the detailed thermodynamic-design methodology for the SE-CHP systems was established and the numerical tool for the design assessment was developed. / <p>QC 20150327</p>