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Selection of Numerical Simulation Methodology for the Small-Size Gas Turbine Engine Cycle

  • AIRCRAFT AND ROCKET DESIGN AND DEVELIOPMENT
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Abstract

The paper analyzes different approaches to the gas turbine engine cycle simulation while designing the computation model of the small-size gas turbine engine flow path. A conventional approach, when the engine is separated into the single units, is compared with a simulation, when it is separated into modules, and with the end-to-end simulation, when all gas turbine engine flow path characteristics are defined in one computation model. It is shown that the type of simulation methodology in terms of computation model formation determines the results in terms of gas-dynamic parameters of the engine.

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Funding

This work was supported by ongoing institutional funding. No additional grants to carry out or direct this particular research were obtained.

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Authors and Affiliations

  1. P.A. Soloviev Rybinsk State Aviation Technical University, ul. Pushkina 53, 152934, Rybinsk, Russia

    V. V. Vyatkov, A. A. Davydov, N. N. Kovaleva & A. M. Toshchakov

Authors
  1. V. V. Vyatkov
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  2. A. A. Davydov
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  3. N. N. Kovaleva
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  4. A. M. Toshchakov
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Correspondence to V. V. Vyatkov.

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Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2023, No. 4, pp. 112 – 118.

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Vyatkov, V.V., Davydov, A.A., Kovaleva, N.N. et al. Selection of Numerical Simulation Methodology for the Small-Size Gas Turbine Engine Cycle. Russ. Aeronaut. 66, 765–773 (2023). https://doi.org/10.3103/S1068799823040165

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  • DOI: https://doi.org/10.3103/S1068799823040165

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