Study of the heat transfer processes in gas turbine blades via finite element method
Franciele Patricia da Silva Muchick1; Sara Del Vecchio1; Flávia de Souza Bastos2
1 Instituto Federal de Educação, Ciência e Tecnologia do Sudeste de Minas Gerais; 2 Universidade Federal de Juiz de Fora
doi:10.20906/CPS/CILAMCE2017-1134
Resumo
The great motivation in conducting research related to heat transfer in gas turbines is based on the fact that, at the present time, there is not much research taking the subject into consideration. This ends up seriously harming the aeronautics industry, which premium for increasing efficiency of the developed thermal machines but is prevented, since it is not possible to raise the inlet temperatures in the turbine stage, which would result in increased thrust consequently increasing the efficiency of the same, with no harm to the operation or safety of the gas turbine. This paper aims to studydifferent configurations for cooling channels of the aeronautical turbine blades via finite element method. In order to pursue this objective an aeronautical turbine blade was developed followingthe boundary conditions initially determined for the turbine being studied. A study was also carried out on the number, size and position of the cooling channels required for better cooling of the turbine. Using the Surrogate Loss System Method, an aerodynamic profile for the blade was calculated and generated according to the initial parameters selected in order to design anoptimum blade for the turbine rotor, aiming the analysis of the existingmethods for cooling it, in pursuance of extend the efficiency of the turbine as a whole.The heat transfer processes were simulated via finite element method. Considering the blades made of stainless steel AISI 310, the blade was submitted to a temperature of 1723.15K, which was the temperature of the inletgases in the turbine module. Then a convectioncooling was investigated into blade channels using thedrained air of the last stage of the compressor, which was at 823.15K.Six different configurations were simulatedincreasing the number of cooling channels and redistributing them along the cross section of the blade, resulting that the most efficient blade is the one that has as many cooling channels as possible, as soon as the mechanical structure integrity was maintained.
Palavras-chave: Gas Turbine; Cooling Channels; Convection; Conduction; Numerical Simulation