Investigation of the Stream Parameter on Output Power of helicopter’s APU

Today, with the advent of gas turbine technology due to pollution, environmental and resource constraints, the industry's urgent need to conduct studies on optimizing their performance and fuel consumption has become more urgent. Identifying combustion system performance on-site and off-site is the first step for optimized future analyzes and designs. This article is the first study on the performance of microturbines that has investigated numerically the T-62T-2A solar microturbine combustion chamber in and out of design. In order to investigate the operating conditions of the engine, the changes of the inlet air flow and inlet temperature to the compressor and the inlet mass flow rate to the chamber have been studied. For this purpose, the numerical method is used to analyze the temperature of the combustion chamber and the current is considered as three-dimensional, stable, incompressible, slimy, turbulent and with radiation. In combustion modeling, a non-pre-combustion combustion model has been modeled for the use of liquid fuel, a fuel spray in the combustion chamber and its evaporation in the Enes Fluent simulator. The results obtained from the numerical solution of the combustion chamber are validated with the results presented by the manufacturer. The results show that, for fuel discharges of less than 0.0125 kg / s, increasing the inlet air temperature leads to increased power, but for higher discharges, it reduces power.