Мақаланы E-mail арқылы жіберу Special features of aerodynamic and thermal improvement of turbine nozzles for advanced gas turbine engines
- Авторлар: Poletaev V.1, Remizov A.1, Vyatkov V.1, Lebedev V.1
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Мекемелер:
- P.A. Solovyov Rybinsk State Aviation Technical University
- Шығарылым: Том 59, № 1 (2016)
- Беттер: 89-94
- Бөлім: 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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Аннотация
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.
Авторлар туралы
V. Poletaev
P.A. Solovyov Rybinsk State Aviation Technical University
Хат алмасуға жауапты Автор.
Email: ad@rsatu.ru
Ресей, ul. Pushkina 53, Rybinsk, 152934
A. Remizov
P.A. Solovyov Rybinsk State Aviation Technical University
Email: ad@rsatu.ru
Ресей, ul. Pushkina 53, Rybinsk, 152934
V. Vyatkov
P.A. Solovyov Rybinsk State Aviation Technical University
Email: ad@rsatu.ru
Ресей, ul. Pushkina 53, Rybinsk, 152934
V. Lebedev
P.A. Solovyov Rybinsk State Aviation Technical University
Email: ad@rsatu.ru
Ресей, ul. Pushkina 53, Rybinsk, 152934
