THE FEATURES OF TURBINE NOZZLE THROAT PARAMETERS ESTIMATION AT GAS TURBINE ENGINE CALCULATION

Abstract

The most often used definition way of the turbine nozzle throat gas parameters at aviation gas turbine engine tests is considered. The major factors influencing a definition error of the temperature and gas flow in turbine nozzle throat of the turbine are analyzed. The results showing influence of most significant of them on estimation results of these parameters are presented. It is shown that the possible error at definition of temperature and gas flow in turbine nozzle throat at typical throat full-capacity discharge can affect considerably a thermal condition estimation of the "hot" engine parts, and also the core air flow. This circumstance in turn can deform essentially representation about the working process realized in the engine.