Email this article Development of the design scheme of cooling for a nozzle vane of high pressure turbine of gas turbine engine
- Authors: Vikulin A.V.1, Yaroslavtsev N.L.1, Chesnova V.A.1
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Affiliations:
- Moscow Aviation Institute (National Research University)
- Issue: Vol 59, No 1 (2016)
- Pages: 58-63
- Section: 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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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.
About the authors
A. V. Vikulin
Moscow Aviation Institute (National Research University)
Author for correspondence.
Email: vav106@yandex.ru
Russian Federation, Volokolamskoe shosse 4, Moscow, 125993
N. L. Yaroslavtsev
Moscow Aviation Institute (National Research University)
Email: vav106@yandex.ru
Russian Federation, Volokolamskoe shosse 4, Moscow, 125993
V. A. Chesnova
Moscow Aviation Institute (National Research University)
Email: vav106@yandex.ru
Russian Federation, Volokolamskoe shosse 4, Moscow, 125993
