Study of Heat Transfer from the Shell of Gas Turbine Plant and Methods of Its Thermal Protection
- 作者: Baklanov A.1, Gimbitskii A.2
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隶属关系:
- AO KMPO
- Tupolev Kazan National Research Technical University
- 期: 卷 62, 编号 3 (2019)
- 页面: 463-468
- 栏目: Aircraft and Rocket Engine Design and Development
- URL: https://journals.rcsi.science/1068-7998/article/view/231059
- DOI: https://doi.org/10.3103/S1068799819030140
- ID: 231059
如何引用文章
详细
The paper presents the results of determining the temperature of gas turbine plant shell. The total heat transfer from the engine is calculated. The thermal protection scheme by blowing air through the porous screen is proposed to reduce the temperature of the gas turbine plant shell as well as to reduce the total heat transfer from the engine to the surrounding compartment space.
作者简介
A. Baklanov
AO KMPO
编辑信件的主要联系方式.
Email: andreybaklanov@bk.ru
俄罗斯联邦, ul. Dement’eva 1, Kazan, Tatarstan, 420036
A. Gimbitskii
Tupolev Kazan National Research Technical University
Email: andreybaklanov@bk.ru
俄罗斯联邦, ul. Karla Marksa 10, Kazan, Tatarstan, 420111