Enviar artigo por via de e-mail Development of the design scheme of cooling for a nozzle vane of high pressure turbine of gas turbine engine
- Autores: Vikulin A.1, Yaroslavtsev N.1, Chesnova V.1
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Afiliações:
- Moscow Aviation Institute (National Research University)
- Edição: Volume 59, Nº 1 (2016)
- Páginas: 58-63
- Seção: Aircraft and Rocket Engine Design and Development
- URL: https://journals.rcsi.science/1068-7998/article/view/229561
- DOI: https://doi.org/10.3103/S1068799816010098
- ID: 229561
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Resumo
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.
Sobre autores
A. Vikulin
Moscow Aviation Institute (National Research University)
Autor responsável pela correspondência
Email: vav106@yandex.ru
Rússia, Volokolamskoe shosse 4, Moscow, 125993
N. Yaroslavtsev
Moscow Aviation Institute (National Research University)
Email: vav106@yandex.ru
Rússia, Volokolamskoe shosse 4, Moscow, 125993
V. Chesnova
Moscow Aviation Institute (National Research University)
Email: vav106@yandex.ru
Rússia, Volokolamskoe shosse 4, Moscow, 125993
