Thesis (MTech(Electrical Engineering))--Cape Technikon, Cape Town,1995 / This thesis describes the research, development and design of one of the most modern generic control and automation system for mini Hydro turbines available in the world. Special emphasis is placed on the Man machine interface. A concept of total dynamic plant and data status representation was pursued. To achieve this, a large amount of graphical animation was incorporated into the design. The end product was to be the most economical and cost effective implementable design available , yet providing the most modern functions and features available in the world market. The system was developed and researched to be generic and applicable to any small Hydro plant. The design can thus be implemented on any suitable PLC and SCADA system and is not dependant on any specific manufactures hardware or software. The main emphasis is laid on functional capability of the design. Utilising this design standard would virtually cut the cost of engineering associated with the design of a Hydro control system by 90%. The design and engineering costs related to a Hydro automation project could typically exceed R 100 000 a for small Hydro plant as this scheme.

Thesis (M. App. Sc.)--Carleton University, 2004. / Includes bibliographical references (p. 144-147). Also available in electronic format on the Internet.

Thesis (Ph.D.(Mechanical Engineering))--University of Pretoria, 2008. / Abstract in English. Includes bibliographical references.

Thesis (Ph. D.)--Ohio State University, 2007. / Full text release at OhioLINK's ETD Center delayed at author's request

No description available.

No description available.

Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990. / Thesis Advisor(s): Netzer, D.W. Second Reader: Shreeve, R.P. "September 1990." Description based on title screen as viewed on December 17, 2009. DTIC Identifier(s): Nitrogen oxide, NOx control, gas turbine combustors, gas turbine fuel additives, soot control, pollution control. Author(s) subject terms: NOx control, gas turbine combustors, gas turbine fuel additives, soot control, pollution control. Includes bibliographical references (p. 65-66). Also available in print.

In a previous work of a similar nature, the performance of a low speed axial turbine with a second stage nozzle was examined with respect to the effect of the variation of tip clearance for various tip shapes. Present findings suggest some interesting phenomena, including the effect of tip clearance on the flow within the rotor and show that poor resolution from a transducer and insufficient data points in the critical tip region, where a high velocity peak was found, were responsible for a number of incorrect conclusions in the original study. In terms of blade tip geometry, a standard flat tip shape was found to deliver only a marginally better performance when compared to a double squealer tip and the two streamlined shapes previously investigated. Although contemporary opinion suggests that a streamlined tip should increase the leakage flow and hence cause greater mixing losses, the machine efficiency was not significantly reduced. This is an exciting result since it suggests that a streamlined tip shape can be used to alleviate the problem of blade tip burnout without significantly reducing machine efficiency. When the single stage performance in the absence of a second nozzle was examined, slightly different trends were obtained. The low entropy tips produced slightly lower mixing loss, suggesting that the internal gap loss is an important parameter in determining the rate at which the leakage jet mixes downstream of the rotor. The flow behind the rotor (ie time averaged) was found to be in remarkable agreement with linear cascade data when time averaged even though the latter did not include any effects of relative motion. An increase in clearance was seen to reduce the Euler work and also to cause a deficit of mass flow across the remainder of the blade right down to the hub. The leakage flow was also seen to induce a flow blockage which resulted in a higher driving pressure across the rotor for the same mass flow rate. As in the previous study, the second stage nozzle efficiency was seen to be independent of tip clearance or tip shape and was moderately better than that of the first nozzle. However, the improvement was not found to be as large, due to a previously undetected very thin ring of high energy leakage fluid. When this is taken into account, the efficiency of the second stage nozzle is comparable to the first. The second nozzle was seen to have a flow straightening effect on the poorly deflected, high energy leakage flow, causing a rapid mixing process within these downstream blade passages. The growth of secondary flow was reduced at both the hub and the tip and this is believed to result in a slight decrease in loss. The outlet flow was closer to design conditions than that of the first stage nozzle. / Thesis (Ph.D.)-University of Natal, Durban, 1996.

No description available.

Thesis (M.App.Sc.) - Carleton University, 2002. / Includes bibliographical references (p. 138-146). Also available in electronic format on the Internet.