Cooling blade temperature state study of a high-temperature gas turbine
Автор: Andreev K.D., Shilov R.A.
Журнал: Международный журнал гуманитарных и естественных наук @intjournal
Рубрика: Технические науки
Статья в выпуске: 5-1 (80), 2023 года.
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The article presents GTN-6U unit first stage nozzle blade cooling system design results and its thermal state. The temperature and cooling film distribution results on the outer blade surface were obtained. Temperature distributions along the blade characteristic sections were obtained and the cooling depth was determined.
Cooling system, temperature, calculation model, boundary conditions, cooling depth
Короткий адрес: https://sciup.org/170199301
IDR: 170199301 | DOI: 10.24412/2500-1000-2023-5-1-34-39
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