Abstract

The gas turbine engine operational performances definition method based on blade–to-blade mathematic simulation of multistage axial compressor and high temperature cooling transonic multistage turbine using flow paths and middle radius blades geometric parameters is shown. The method allows to take into account air bypass and bleeding from compressor for the cooling and its blowing into turbine and their influence on the engine parameters.
As example, attained by calculation way the results of turbo-shaft engine operational performances and air by pass bleeding from compressor influence on the engine specific parameters, efficiency and stability margin are represented.