Email this article Special features of aerodynamic and thermal improvement of turbine nozzles for advanced gas turbine engines
- Authors: Poletaev V.A.1, Remizov A.E.1, Vyatkov V.V.1, Lebedev V.V.1
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Affiliations:
- P.A. Solovyov Rybinsk State Aviation Technical University
- Issue: Vol 59, No 1 (2016)
- Pages: 89-94
- Section: Aircraft and Rocket Engine Design and Development
- URL: https://journals.rcsi.science/1068-7998/article/view/229586
- DOI: https://doi.org/10.3103/S1068799816010141
- ID: 229586
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Abstract
Some results of investigating the geometrical and jet impact on secondary flows and thermal state of cooled inter-profile end surfaces of gas turbine engine nozzles have been set forth under different secondary flows interaction degree in a blade channel.
About the authors
V. A. Poletaev
P.A. Solovyov Rybinsk State Aviation Technical University
Author for correspondence.
Email: ad@rsatu.ru
Russian Federation, ul. Pushkina 53, Rybinsk, 152934
A. E. Remizov
P.A. Solovyov Rybinsk State Aviation Technical University
Email: ad@rsatu.ru
Russian Federation, ul. Pushkina 53, Rybinsk, 152934
V. V. Vyatkov
P.A. Solovyov Rybinsk State Aviation Technical University
Email: ad@rsatu.ru
Russian Federation, ul. Pushkina 53, Rybinsk, 152934
V. V. Lebedev
P.A. Solovyov Rybinsk State Aviation Technical University
Email: ad@rsatu.ru
Russian Federation, ul. Pushkina 53, Rybinsk, 152934
