Features of design calculation of compressor spool flow path of a twin-shaft gas turbine engine core on the basis of 1D and 2D models of their working process

Abstract

The features of the stages of parameter design calculation for the formation of the initial design of the flow path of the compressor spool of a twin-shaft engine core of a gas turbine engine are presented and substantiated. The article contains recommendations for choosing values of the pump head coefficient, efficiency and other important parameters for the stages of medium-pressure and high-pressure spools at the stage of thermodynamic calculation. At the stage of design gas-dynamic calculation of the compressor at the middle diameter, typical distributions of axial velocity component and degree of reaction along the flow path of compressor spools should be taken into consideration. At the same time, it is necessary to provide requirements for reducing the flow velocity and static pressure coefficients in the rotor wheels and stator blades, head coefficients and Stepanov coefficients. The design gas-dynamic calculation of the compressor along the radius of the flow path is characterized by a variety of flow swirl laws at the inlet to the rotor wheels, distributions of the pressure increase and efficiency over the height of the blades. In conclusion, an example of a three-dimensional model of a compressor flow path taking into consideration the features of design calculation of the parameters of compressor spools of a twin-shaft engine core of a gas turbine engine on the basis of the appropriate flow path diagram in the meridional plane is presented.

Keywords

• aviation gas turbine engine
• twin-shaft engine core
• compressor spools
• flow path