Maurente, André Jesus SoaresAlves, Camilo Gustavo Araújo2019-05-062019-05-062019-02-11ALVES, Camilo Gustavo Araújo. Análise da transferência de calor por radiação em combustor de Turbina Turbo-FAN pelo Método LBL. 2019. 72f. Dissertação (Mestrado em Engenharia Mecânica) - Centro de Tecnologia, Universidade Federal do Rio Grande do Norte, Natal, 2019.https://repositorio.ufrn.br/jspui/handle/123456789/26976The turbines are thermal machines and can be classified as stationary or non-stationary. The industrial application of non-stationary turbines that has received more attention at the moment is the aeronautical turbine. The turbo-fan turbine is the type of aeronautical turbine most used in the transport of passengers and cargo. As a thermal machine the turbo-fan is an equipment subject to the dynamics associated with heat transfer. The analysis of this type of heat transfer allows a better selection of the materials used in the manufacture of aeronautical turbines, control of the unwanted products of combustion and greater safety in its operating regime (related to the control of the Hot-Streaks). The objective of this research is to analyze the radiative transfer of heat inside the combustor of a turbo-fan turbine with combustion parameters and geometry predefined. The gradient of temperature and concentration of the emitting and absorber species of radiative energy were used in the analysis were obtained by Glenn Research Center (NASA), which simulated combustion, turbulence and convection in the combustion chamber, but ignored the radiative transfer of heat. The analysis done in the work was for a one-dimensional case. The quantification of the converted heat was done by computational analysis, applied on a unidimensional line inside the turbine combustor, which was divided in 25 groups with different temperatures and concentrations of three different participating gases (𝐶𝑂, 𝐻2𝑂 𝑒 𝐶𝑂2). The database used in this research was HITEMP2010 which provided information of each participating gas. Based on these data the Line-by-Line (LBL) method was used to obtain the characteristic absorption coefficients for each participating substance, setting the pressure at 3 atm. The absorption coefficients along with the absorption cross sections were used in the Radiation Transfer Solution (using the Finite Volumes method) providing the radiative flux and divergent flux on the conditions that were established. This research will allow a better understanding of the distribution and quantification of the heat flux in the engine, generating a better knowledge of the dynamics of combustion, better choice of materials of the device and greater safety against failures inherent to the equipment. Discontinuities were observed in the radiative heat transfer curves due to the dynamic processes occurring in the combustor, where the radiative heat flux in the region immediately after the combustor burner presented a value of approximately 24 𝑀𝑊/𝑚2 and in the region of flow directing fins of 21 𝑀𝑊/𝑚2 for the mixture of the substances, where the majority influence was 𝐻2𝑂.Acesso AbertoTransferência de calor por radiaçãoTurbina aeronáuticaEquação da Transferência RadiativaMétodo Linha-por-LinhamasterThesisCNPQ::ENGENHARIAS::ENGENHARIA MECANICA