Modelling & numerical exploration of pulsejet engine using eddy dissipation combustion model

Abstract

The pulsejet engine is relatively simple engine used in missiles but the combustion modeling of pulsejet engine is relatively complex through numerical analysis procedure. The current research investigates the application of eddy dissipation model in analyzing the combustion and thus thrust generation. Three different fuel inlet designs of pulsejet engine are considered for analysis i.e. single inlet, three inlet and five inlets. The Jet Air combustion is modeled under pseudo static steady state conditions. The CFD analysis is conducted using ANSYS CFX analysis package and CAD model is developed in PTC Creo design software. The static enthalpy, thrust and velocity are determined for all the three designs. The research findings have shown that the fuel to air ratio has significant effect on thrust generation from pulsejet engine. The turbulence kinetic energy is highest near the walls and near nozzle which reduces as we move away from it.