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Development of the design scheme of cooling for a nozzle vane of high pressure turbine of gas turbine engine

  • Aircraft and Rocket Engine Design and Development
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Abstract

The design schemes of cooling for the nozzle blades of high-temperature gas turbines are considered. The results of the thermal and hydraulic tests for the cooling systems of the nozzle vanes are presented. The prospective cooling system of the nozzle vanes of low and high pressure turbines is developed and presented. The test results for the vane with proposed design are presented.

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References

  1. Vikulin, A.V., Popov, V.G., Yaroslavtsev, N.L, Chesnova, V.A., and Pobezhimovskii, E.V., Teplovye ispytaniya i dovodka okhlazhdaemykh lopatok gazovykh turbin (Thermal Tests and Debugging of Cooled Gas Turbine Blades), Kostroma: OOO KPD, 2012.

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Authors and Affiliations

  1. Moscow Aviation Institute (National Research University), Volokolamskoe shosse 4, Moscow, 125993, Russia

    A. V. Vikulin, N. L. Yaroslavtsev & V. A. Chesnova

Authors
  1. A. V. Vikulin
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  2. N. L. Yaroslavtsev
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  3. V. A. Chesnova
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Corresponding author

Correspondence to A. V. Vikulin.

Additional information

Original Russian Text © A.V.Vikulin, N.L. Yaroslavtsev, V.A. Chesnova, 2016, published in Izvestiya VUZ, Aviatsionnaya Tekhnika, 2016, No. 1, pp. 54—58.

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Vikulin, A.V., Yaroslavtsev, N.L. & Chesnova, V.A. Development of the design scheme of cooling for a nozzle vane of high pressure turbine of gas turbine engine. Russ. Aeronaut. 59, 58–63 (2016). https://doi.org/10.3103/S1068799816010098

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  • DOI: https://doi.org/10.3103/S1068799816010098

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