Abstract

This article presents the results of computations on pilot-based turbulent methane/air co-flow diffusion flames under the influence of the preheated oxidizer temperature ranging from 293 to 723 K at two operating pressures of 1 and 3 atm. The focus is on investigating the soot formation and flame structure under the influence of both the preheated air and combustor pressure. The computations were conducted in a 2D axisymmetric computational domain by solving the Favre averaged governing equation using the finite volume-based CFD code Ansys Fluent 19.2. A steady laminar flamelet model in combination with GRI Mech 3.0 was considered for combustion modeling. A semi-empirical acetylene-based soot model proposed by Brookes and Moss was adopted to predict soot. A careful validation was initially carried out with the measurements by Brookes and Moss at 1 and 3 atm with the temperature of both fuel and air at 290 K before carrying out further simulation using preheated air. The results by the present computation demonstrated that the flame peak temperature increased with air temperature for both 1 and 3 atm, while it reduced with pressure elevation. The OH mole fraction, signifying reaction rate, increased with a rise in the oxidizer temperature at the two operating pressures of 1 and 3 atm. However, a reduced value of OH mole fraction was observed at 3 atm when compared with 1 atm. The soot volume fraction increased with air temperature as well as pressure. The reaction rate by soot surface growth, soot mass-nucleation, and soot-oxidation rate increased with an increase in both air temperature and pressure. Finally, the fuel consumption rate showed a decreasing trend with air temperature and an increasing trend with pressure elevation.

Highlights

  • Introduction iationsGas turbine combustors usually operate at elevated pressure, and the oxidizer supplied at the inlet is mostly in preheated conditions

  • When it comes to comparing the cases between 1 and 3 atm pressure for a fixed reactant temperature, the iso-line of axial velocity at atmospheric pressure was found at a greater height than 3 atm

  • The velocities at the inlet of both the fuel and co-flow jet were decreased as the pressure was increased from 1 to 3 atm for a fixed air temperature

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Summary

Introduction

Gas turbine combustors usually operate at elevated pressure, and the oxidizer supplied at the inlet is mostly in preheated conditions. This helps in improving the thermal efficiency as well as decreasing the size of the combustor. The gas turbine combustor operates at a high turbulence level. It is vital to examine soot formation under these circumstances. Soot is generated due to the incomplete combustion of hydrocarbon fuel. The presence of soot in the combustor leads to a decrease in combustor efficiency and brings about a lot of environmental pollution

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