Blade-to-blade modeling of turbomachinery, based on methods for developing the parameters and characteristics of modern gas turbine engines, enables the resolution of a wide range of theoretically and practically significant problems in engine design, development, and operation. It also improves the accuracy of performance calculations. This article investigates thermogasdynamic processes within the flow part of a gas turbine engine and its elements, focusing in particular on a multi-stage gas turbine. The study is based on a method for developing the parameters and operational characteristics of a gas turbine engine, with a key component being a module for the final development of parameters of a multi-stage cooled gas turbine within the engine system. The object of investigation is a high-temperature cooled, multi-stage axial gas turbine for aircraft engines. The main result of this work is the development of a method for incremental sizing of parameters for a cooled, multi-stage turbine, along with a corresponding software package. This method was tested based on real development results. The investigation examined the parameters of the turbine stage blade row and the operating mode associated with rotor speed, showing the influx of impingement on the blade, observed only under specific rotor configurations at the QCD stage. The scientific and practical novelty of this work lies in its comprehensive approach to modeling the operation of a turboshaft gas turbine engine, providing a complete description of the compressor and turbine. This modeling is not feasible without a real-time simulation of thermogas-dynamic phenomena in the flow part of a multi-stage gas turbine, particularly in a single-stage plant behind the middle radius with the arrangement of cooling methods and the place of supply depending on the cooling system, as well as the temperature and losses, the emergence of critical operating modes when the blade screws twisting, which significantly influence turbine performance. The process is described using strict conservation laws for highly compressed gases, under conditions that ensure realistic flow power, consistent with values reported in the literature. The utility of the developed method, implemented in a dedicated software complex, will be connected to the complex of programs for the development of the characteristics of the gas turbine engine.


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    Titel :

    Turboshaft gas turbine engine thermodynamics calculation method based on blade machine blade to blade description.Part III. Turbine parameters calculation


    Beteiligte:


    Erscheinungsdatum :

    2025




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Unbekannt




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