Development of the design scheme of cooling for a nozzle vane of high pressure turbine of gas turbine engine
- 作者: Vikulin A.1, Yaroslavtsev N.1, Chesnova V.1
-
隶属关系:
- Moscow Aviation Institute (National Research University)
- 期: 卷 59, 编号 1 (2016)
- 页面: 58-63
- 栏目: 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
如何引用文章
详细
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.
作者简介
A. Vikulin
Moscow Aviation Institute (National Research University)
编辑信件的主要联系方式.
Email: vav106@yandex.ru
俄罗斯联邦, Volokolamskoe shosse 4, Moscow, 125993
N. Yaroslavtsev
Moscow Aviation Institute (National Research University)
Email: vav106@yandex.ru
俄罗斯联邦, Volokolamskoe shosse 4, Moscow, 125993
V. Chesnova
Moscow Aviation Institute (National Research University)
Email: vav106@yandex.ru
俄罗斯联邦, Volokolamskoe shosse 4, Moscow, 125993