Combustor Characteristics under Dynamic Condition during Fuel – Air Mixing using Computational Fluid Dynamics

A gas turbine can combustor is designed to burn the fuel efficiently while reducing the NOx and CO emissions, and lowering the wall temperature. Environmental challenges with gas turbine include low levels of NOx, CO and soot amongst other pollutants. There is a need for new concepts and technology to satisfy the pollutants emission regulations and to enhance energy conservation. Specifically, ultra-low NOx combustor technology is required to meet the ozone depletion challenge. Researchers now face a challenge of developing dry low-NOx emitting stationary and aero engines. However, any concept for environmental pollution control requires a detailed understanding of the physical and the chemical processes that occur during combustion. In this paper, a three dimensional numerical investigation of the Combustion methane air mixture in a gas turbine can combustor is carried out by using ANSYS. The objective of the study is to understand the combustion phenomena at different planes. The various parameters like air-fuel ratio, velocity of primary air inlet are used to investigate the effects on parameters like combustion chamber on different plane performance and emission. A premixing tube is augmented with the combustion chamber which has a primary air inlet port and three gaseous fuel inlet ports. Air–methane mixture is considered to enter the combustion zone with inlet swirl. The homogeneity of mixture before and after swirl and other important conditions are calculated from simulation and are reported with the help ANSYS FLUENT. Weighted averages of velocity magnitude distribution and mass fractions of methane have been studied at different planes.