Examination of heat load at different zones of a Nimonic alloy combustor liner of different configurations by finite element method

Abstract

In modern ages, the usage of gas turbine systems in aviation and power sectors has been increased tremendously. To achieve the desirable output, the components used in the gas turbine systems are heated to high temperatures. The increase in temperature may increase the heat load on the components which in turn increase the thermal stress and the component may undergo thermal expansion. Due to the exposure of these components to heat regularly, it may also increase the fatigue and creep of the material, thereby the life of the materials used for the fabrication of these components may decrease. As the life of the components decrease, the efficiency of the gas turbine system also decreases. Combustor liner of the gas turbine system undergo high thermal stress because of the combustion of fuel and air inside it. Temperature distribution and the heat load on the combustor is mandatory to make the design of engine reliable. The present work focuses on the design of combustor liner with different configurations for a gas turbine engine used for land-based power generation. The distribution of temperature at the primary. Secondary and dilution zones of the combustor liner for proposed configurations was analysed using ANSYS. The heat load at the zones of the combustor liner was also studied with the help of ANSYS. The results observed in the analysis helps out to study the effects of design variation on temperature distribution and heat load at different zones of the liner. The results also helped in the selection of a best configuration with low heat load at different zones of the liner.