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Cooled two-stage GTE turbine with a tubular or tubular-annular combustion chamber

  • Aircraft and Rocket Engine Design and Development
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Abstract

A scheme of the nozzle blade arrangement in the two-stage GTE turbine is described taking into account peripheral periodic inhomogeneity of the temperature field.

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References

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  3. Lapshin, K.L. and Sadovnichii, V.N., Experimental Determination of Peripheral Wash of Edge Guide Vane Wake in the Turbine Stage, Izv. Vuz. Energetika, no. 11, pp. 109–111, 1980.

  4. Lokai, V.I., Maksutova M.Kh., and Strunkin, V.A., Gazovye turbiny dvigatelei letatel’nykh apparatov (Gas Turbines of Flight Vehicle Engines), Moscow: Mashinostroenie, 1991.

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Authors and Affiliations

  1. Tupolev State Technical University, Kazan, Russia

    R. S. Agachev, V. A. Sychenkov & P. A. Stepanov

Authors
  1. R. S. Agachev
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  2. V. A. Sychenkov
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  3. P. A. Stepanov
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Additional information

Original Russian Text © R.S. Agachev, V.A. Sychenkov, P.A. Stepanov, 2008, published in Izvestiya VUZ. Aviatsionnaya Tekhnika, 2008, No. 1, pp. 67–69.

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Agachev, R.S., Sychenkov, V.A. & Stepanov, P.A. Cooled two-stage GTE turbine with a tubular or tubular-annular combustion chamber. Russ. Aeronaut. 51, 90–93 (2008). https://doi.org/10.3103/S1068799808010157

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  • DOI: https://doi.org/10.3103/S1068799808010157

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