Modern combustion turbines have several applications: power stations, naval, aeronautical and oil industry. Aeronautical applications seek reduction of pollutant emissions using mixtures of conventional jet fuels with biofuels and synthetic fuels. Due to the restrictions of natural gas and other oil fuels supply for the generation of electricity, the use of alternative fuels in stationary gas turbines is being seriously considered. Generally, all liquid and gaseous fuels from biomass, syngas, biogas, refinery gas and other unconventional sources are considered as alternative fuels. In the last years, with the objective of making the industrial and aeronautical process in harmony with the current environmental laws around the world, much research on the use of these alternative fuels in gas turbines is in progress. Gas turbines are thermal machines with the great advantage of being capable of successfully burning a large variety of fuels in a continuous combustion process. Gas turbine combustion chambers with this ability are referred as fuel flexible gas turbine combustors. This thesis aims at describing a methodology for sizing fuel flexible gas turbine combustors and, additionally, analyzing the reacting flow in these designed combustion chambers. The design of the fuel flexible gas turbine combustors is based on the reaction mechanisms, reactor network and stability loops approach simultaneously with numerical methods as Newton-Raphson, LU factorization, splines and inverse Lagrange polynomials. A computational tool has been developed for the combustor sizing and reacting flow analysis. The zero and one-dimensional models are based on the methodology developed by Lefebvre, Melconian e Modak. The thermokinetic, flammability limits and reaction mechanisms models are based on the methodology developed by Gordon and McBride and other authors. The study of the combustion efficiency and stability loops for the studied fuels and their influence on the production of pollutant emissions under several operating conditions is presented. Useful information is generated at the design stage of a fuel flexible gas turbine combustion chamber, which may be used to alter the pollutant emissions at very early stage of the design.
| Identifer | oai:union.ndltd.org:IBICT/oai:agregador.ibict.br.BDTD_ITA:oai:ita.br:2248 |
| Date | 08 April 2013 |
| Creators | Washington Orlando Irrazabal Bohorquez |
| Contributors | João Roberto Barbosa |
| Publisher | Instituto Tecnológico de Aeronáutica |
| Source Sets | IBICT Brazilian ETDs |
| Language | English |
| Detected Language | English |
| Type | info:eu-repo/semantics/publishedVersion, info:eu-repo/semantics/doctoralThesis |
| Format | application/pdf |
| Source | reponame:Biblioteca Digital de Teses e Dissertações do ITA, instname:Instituto Tecnológico de Aeronáutica, instacron:ITA |
| Rights | info:eu-repo/semantics/openAccess |
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