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The problem of determining the design parameters of the gas turbine engine for a helicopter

  • Aircraft and Rocket Engine Design and Development
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Abstract

In this paper, an approach to selecting the rational values for the operation procedure parameters in a gas turbine engine with free turbine (FGTE) in terms of optimization is considered taking into account changes in the required power for a helicopter flight along a predetermined path as well as in fuel weight.

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References

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Authors and Affiliations

  1. Samara State Aerospace University, shosse Moskovskoe 34, Samara, 443086, Russia

    V. A. Grigor’ev & A. O. Zagrebel’nyi

Authors
  1. V. A. Grigor’ev
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  2. A. O. Zagrebel’nyi
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Corresponding author

Correspondence to V. A. Grigor’ev.

Additional information

Original Russian Text © V.A. Grigor’ev, A.O. Zagrebel’nyi, 2014, published in Izvestiya VUZ. Aviatsionnaya Tekhnika, 2014, No. 3, pp. 41–43.

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Grigor’ev, V.A., Zagrebel’nyi, A.O. The problem of determining the design parameters of the gas turbine engine for a helicopter. Russ. Aeronaut. 57, 272–275 (2014). https://doi.org/10.3103/S106879981403009X

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  • DOI: https://doi.org/10.3103/S106879981403009X

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