• THE GAS TURBINE ENGINES OPERATIONAL PERFOMANCES MATHEMATIC SIMULATION METHOD

    Machines. Technologies. Materials., Vol. 9 (2015), Issue 8, pg(s) 49-52

    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.

  • METHODS OF AVIATION GAS TURBINE ENGINES COMPRESSORS COMPUTATIONAL INVESTIGATIONS

    Machines. Technologies. Materials., Vol. 9 (2015), Issue 8, pg(s) 53-56

    The prediction methods for calculating of different compressor objects developed at the department of aircraft engines theory of National Aerospace University named after N. E. Zhukovsky "Kharkov Aviation Institute" are presented. Results of computational studies for various compressor objects such as high-pressure fan stage, multistage axial compressors of GTE in a wide range of flow rates and rate of are rotation modes and high pressure centrifugal stage with taking into account the air – bleeding and bypass from compressor setting shown. The Mach number flow isolines near the stability boundary, on the line of operating modes and near the compressor locking are demonstrated. Numerical investigation results of sub- and transonic flow fields and summary performances in high pressure centrifugal stage are presented and the flow features in its elements and its modification results are examined.