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Advisor(s)
Abstract(s)
O aumento dos requisitos de eficiência dos motores quer por razões económicas quer por
razões ambientais faz com que seja cada vez mais importante otimizar o seu
funcionamento. O tipo de motor mais utilizado em aviação é o motor turbofan com o tipo
de câmara de combustão anelar. Assim, o objetivo deste trabalho consiste na otimização
de uma câmara de combustão anelar para um motor turbofan de pequenas dimensões.
O trabalho inicia-se com o estado da arte, onde se introduz as características de um
motor turbofan, as suas configurações e uma breve descrição dos seus componentes. De
seguida apresenta-se os diversos tipos de câmaras de combustão, e explora-se com algum
detalhe o projeto de difusores juntamente com a análise aerodinâmica de uma câmara
de combustão. O capítulo termina com a exposição de alguns modelos de combustão
utilizados no projeto de câmaras, e uma breve referência às emissões de gases poluentes.
O objetivo do caso de estudo é desenvolver uma câmara de combustão tendo por base o
trabalho de Mark Priyant e A. Selwyn. A metodologia utilizada foi exclusivamente
aerodinâmica, onde partindo das condições de pressão, temperatura e caudal na saída
do compressor, dimensionou-se a câmara. O algoritmo seguido resulta da combinação
de várias fontes, das quais se destacam o livro “Gas Turbine Combustion Alternative Fuel
Emissions” de Arthur Lefebvre e Dilip Ballal, que compila diversos artigos utilizados, e o
artigo “Desing of laboratory annular combustor” de Satish Dharmalingam e Kartik
Kothari. Após o dimensionamento foi construído um modelo 3D em SolidWorks e fez-se
uma simulação 2D recorrendo ao software Ansys Fluent apenas da parte interior da
câmara. Os resultados obtidos de temperatura, pressão e velocidade foram comparados
com os resultados publicados por Priyant e Selwyn, apresentado uma melhoria
significativa resultante de uma menor perda de pressão.
The increase in engine efficiency requirements by economic and environmental reasons, has made it crucial to optimize the engine operation. The most common engine type in aviation is the turbofan engine and the most common combustion chamber is the annular configuration, so, the objective of this work is to optimize an annular combustion chamber for a small turbofan engine. This work begins by presenting the characteristics of the turbofan engine including its various configurations and a brief explanation on its components. It then discusses the different types of combustion chambers followed by the diffusor design and the aerodynamical analysis of the combustor. The end of this this chapter briefly addresses the combustion models used in design and the emissions resulting from the combustion process. The case study seeks to develop a combustion chamber based on the work of Mark Priyant e A. Selwyn. The methodology used was exclusively aerodynamical starting from the pressure, temperature and mass flow at the compressor outlet it was possible to determine the dimensions of the combustor. The algorithm followed, comes from a combination of various sources but mainly from the book “Gas Turbine Combustion Alternative Fuel Emissions” by Arthur Lebfebvre and Dilip Ballal, which compiles many papers used on this study, and the paper “Desing of laboratory annular combustor” by Satish Dharmalingam and Kartik Kothari. After the calculations, a 3D model was created using SolidWorks and a 2D simulation of the interior of the chamber was done using Ansys Fluent, the results were then compared to the results obtained by Priyant e Selwyn revealing an improvement.
The increase in engine efficiency requirements by economic and environmental reasons, has made it crucial to optimize the engine operation. The most common engine type in aviation is the turbofan engine and the most common combustion chamber is the annular configuration, so, the objective of this work is to optimize an annular combustion chamber for a small turbofan engine. This work begins by presenting the characteristics of the turbofan engine including its various configurations and a brief explanation on its components. It then discusses the different types of combustion chambers followed by the diffusor design and the aerodynamical analysis of the combustor. The end of this this chapter briefly addresses the combustion models used in design and the emissions resulting from the combustion process. The case study seeks to develop a combustion chamber based on the work of Mark Priyant e A. Selwyn. The methodology used was exclusively aerodynamical starting from the pressure, temperature and mass flow at the compressor outlet it was possible to determine the dimensions of the combustor. The algorithm followed, comes from a combination of various sources but mainly from the book “Gas Turbine Combustion Alternative Fuel Emissions” by Arthur Lebfebvre and Dilip Ballal, which compiles many papers used on this study, and the paper “Desing of laboratory annular combustor” by Satish Dharmalingam and Kartik Kothari. After the calculations, a 3D model was created using SolidWorks and a 2D simulation of the interior of the chamber was done using Ansys Fluent, the results were then compared to the results obtained by Priyant e Selwyn revealing an improvement.
Description
Keywords
Análise Aerodinâmica Ansys Fluent Câmara Anelar Difusor Motor Turbofan Solidworks