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Abstract(s)
As turbinas de gás têm uma ampla aplicação no setor industrial tanto para o
fornecimento da energia elétrica como também propulsiva. Sendo este um trabalho no
ramo da indústria aeronáutica o foco esteve mais centrado na formação de energia
propulsiva tendo em conta os motores Turbofan, sendo esse uma variante das turbinas
de gás. A conversão em energia propulsiva no Turbofan passa por diversas etapas de
entre as quais a combustão. Para tal é necessária uma câmara de combustão onde
ocorre todo o processo de combustão, ou seja, o combustível é injetado sobre o ar
comprimido para uma posterior mistura. Neste seguimento, o presente trabalho tem
como objetivo o cálculo para a determinação das dimensões dos diversos componentes
que constituem uma câmara de combustão anelar, uma vez que estes podem ser de três
tipos diferentes (tubolar, anelar, tubo-anelar). O método do cálculo basea-se na
aplicação da equação proposta por Levebvre e Ballal para o dimensionamento de uma
câmara de combustão anelar, propondo os valores dos parâmetros inicias, tais como a
pressão e temperatura de entrada do ar comprimido na câmara de combustão.
Gas turbines have a wide application in the industrial sector for both the supply of electricity and also propulsive. This work is focused on the aeronautical industry. The study was on the formation of propulsive energy in Turbofan engines, which are a variant of gas turbines. The conversion into propulsive energy, considering the Turbofan engines, goes through several stages, being one the combustion. For this it is necessary a combustion chamber where the entire combustion process occurs, that is, the fuel is injected into the compressed air for a subsequent mixture. In this follow-up, the present work aims to calculate the determination of the dimensions of the various components that constitute a annular combustion chamber, since they can be of three different types (tubular, annular, annular-tube). The calculation method is based on the application of the equation proposed by Levebvre and Ballal for the dimensioning of an annular combustion chamber, proposing the values of the initial parameters, such as the pressure and inlet temperature of compressed air entering in the combustion chamber.
Gas turbines have a wide application in the industrial sector for both the supply of electricity and also propulsive. This work is focused on the aeronautical industry. The study was on the formation of propulsive energy in Turbofan engines, which are a variant of gas turbines. The conversion into propulsive energy, considering the Turbofan engines, goes through several stages, being one the combustion. For this it is necessary a combustion chamber where the entire combustion process occurs, that is, the fuel is injected into the compressed air for a subsequent mixture. In this follow-up, the present work aims to calculate the determination of the dimensions of the various components that constitute a annular combustion chamber, since they can be of three different types (tubular, annular, annular-tube). The calculation method is based on the application of the equation proposed by Levebvre and Ballal for the dimensioning of an annular combustion chamber, proposing the values of the initial parameters, such as the pressure and inlet temperature of compressed air entering in the combustion chamber.
Description
Keywords
Câmara de Combustão Projeto Turbina de Gás Turbofan