Improved Algorithm for Design Thermodynamic Calculation of Axial Turbomachinery Parameters of Core Engine of a Single-shaft Turboprop Engine

The paper proposes an improved algorithm for thermodynamic calculation of the turbomachinery of a single-shaft core engine of a turboprop engine, based on null-dimensional and one-dimensional models of the working process of compressors and turbines. it is based not only on the balance of working fluid flow rates in the compressor and turbine, but also on the balance of flow rates extracted from the compressor working fluid and air supplied mainly to the turbine and engine nozzle to cool the parts of the assembly units. the algorithm assumes calculation of multistage compressors with air bleeding behind both the last and intermediate stages. calculation of a multistage turbine takes into account air supplies for cooling stator and rotor blades, rotor wheel discs in sections at their inlet and outlet. the algorithm of the thermodynamic calculation of the core engine turbomachinery is presented together with the thermodynamic calculation of the whole engine and with the first step of the design calculation of turbomachinery parameters, i.e., coordination of the main parameters of the turbomachinery and formation of the preliminary shape of their flow path in the meridional plane.