THE TURBINE INLET TEMPERATURE AND COMPRESSOR PRESSURE RATIO, THE SIAMESE TWINS OF THE GAS TURBINE ENGINES

Abstract

When we read the technical data of any kind of gas turbine engines in most cases besides the performance data we get two important data, namely the Turbine Inlet Temperature (TIT) and Compressor Pressure Ratio (CPR) usually for take-off rate of power. But considering a certain TIT there is a range of CPR which is suitable for this TIT. This range of CPR depends on the TIT itself but the engine component efficiencies also has effect on the possible CPR. In this paper we intended to examine how this range of CPR can be determined, the range itself, how it is affected by the component efficiencies and the operational point of today existing turboshaft engines between the minimum and maximum possible CPR-s. To answer these questions we developed a gas turbine thermal mathematical model.