Отправить статью по E-mail Study of Heat Transfer from the Shell of Gas Turbine Plant and Methods of Its Thermal Protection
- Авторы: Baklanov A.1, Gimbitskii A.2
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Учреждения:
- AO KMPO
- Tupolev Kazan National Research Technical University
- Выпуск: Том 62, № 3 (2019)
- Страницы: 463-468
- Раздел: 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
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Аннотация
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.
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Об авторах
A. Baklanov
AO KMPO
Автор, ответственный за переписку.
Email: andreybaklanov@bk.ru
Россия, ul. Dement’eva 1, Kazan, Tatarstan, 420036
A. Gimbitskii
Tupolev Kazan National Research Technical University
Email: andreybaklanov@bk.ru
Россия, ul. Karla Marksa 10, Kazan, Tatarstan, 420111
