Dissertação (mestrado) - Universidade Federal de Santa Catarina, Centro Tecnologico / Made available in DSpace on 2016-01-08T19:02:40Z (GMT). No. of bitstreams: 1 99947.pdf: 2226338 bytes, checksum: 5afa9525fd94e9133462bbab2e19ecef (MD5) Previous issue date: 1994 / Mecanismo de reação e os efeitos térmicos na combustão do benzeno em combustor tubular simples e outro do tipo trocador de calor em contra-corrente. Estuda as vantagens comparativas dos combustores, o efeito do pré-aquecimento da mistura de reagente pelos produtos da reação química, bem como a influência da adição de um hidrocarboneto mais simples na combustão do benzeno.

The combustors for gas turbines have been traditionally designed through trial and error, which is a time consuming and expensive process. With the development of computers and new simulation techniques the design process has been improved considerably. However, the design of combustors for gas turbines still remains an iterative process, which requires a broad knowledge of engine operating conditions and the interaction of their components with the engine components. This work presents the establishment of a methodology for preliminary design for gas turbine combustor, based on the methodology proposed by Melconian e Moldak and the application of a chemical reactors network (CRN), this last one in order to establish the temperature profile of the gases into combustor. Originally, the methodology proposed by Melconian e Moldak uses kerosene as fuel. For this reason, the proposed methodology in this work was adapted to consider different types of fuel. This methodology is capable to set the basic geometric parameters and providing a basic configuration of a combustor considering changes in operational loads. Some cases have been developed, which allowed verifying the implementation of the proposed methodology and the CRN. The first case was used as validation method and was employing a multi-can combustor type, which operates with kerosene as fuel based on example proposed by Melconian e Moldak. The second case corresponds to an annular combustor for an aircraft engine which operates with kerosene, natural gas and ethanol. For each of these fuels was carried out a preliminary design of combustor. The third case is a can annular combustor for application in an industrial gas turbine using natural gas, ethanol and kerosene as fuels. A step by step design methodology is presented in this work. It is important to mention that the proposed methodology is for conventional combustors.