Gas Turbine Engine Combustors and the Estimation of their Pressure Loss

Abstract

Combustor is a crucial component of the gas turbine engine through which the chemical energy of the fuel is converted into thermal energy with minimal pressure loss and maximal efficiency meanwhile the emitted harmful pollutants and the deposit must be minimised. That condition can be achieved through highly turbulent flow which description with numerical methods is difficult even today. In accordance with it the design of combustor is based more empiricism collected from the previous experiences and tests. In this paper we deal with the pressure loss in the combustors examining what kind of methods, empirical equations can be used to predict the estimated value of pressure loss. Using the Fanno and Rayleigh line flow we tried to determine the pressure loss in the combustor of TV2-117A turboshaft engine.