Karpenko O. Method of Analysis of the Gas-Thermodynamic Properties of the Turboshaft Gas Turbine Engine with Axial Multistage Compressor Blade Rows Description

The object is turboshaft gas turbine engine. The aim is steady state condition turboshaft engine gas-thermodynamic parameters analysis method creation on the on basis of component-based engine description and stage-by-stage descriptions of the multi-stage axial compressor flow. The novelty consists in the first turboshaft engine gas-thermodynamic parameters on the steady state condition designing method proposition; first methodical bases for determining gas turbine engine gas-thermodynamic parameters on different conditions taking into account air bypass, axial compressor blade rows and setting geometrical parameters changing, variable guide vanes low of control changing are developed. The results are determine gas turbine engine gas-thermodynamic parameters on different conditions taking into account air bypass, axial compressor blade rows and setting geometrical parameters changing, variable guide vanes low of control changing, the quality of designing improvement. The branch is gas turbine engineering.