Experimental and Numerical Investigation of Non-reacting Flow in Can Combustor for Microgas Turbine Engine

Abstract

Generally, microgas turbines are in the range of 30–200 kW. So, here it is proposed to develop a microgas turbine engine with a capacity of 3 kW which will have applications in unmanned aerial vehicle (UAV) and standalone power generation for domestic use. In this study, the behavior of non-reacting flow pattern inside a swirl stabilized can combustor is studied. Total pressure loss, which is an important performance parameter, is predicted numerically and compared with that from experiments. Good agreement is achieved between experimental and numerical results. The combustor total pressure drop was found to be negligible; in the range of 0.002–0.06% at an inlet velocity ranges from 1.7 to 10.19 m/s. Flow pattern indicates strong vortex formation due to secondary air entrainment inside the flame tube.