Samara University Repository
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This is an open electronic archive created to preserve and disseminate the scientific results of our university. The works of researchers, faculty members, and students are available to everyone for academic and research purposes.
The repository contains dissertations, research articles, educational and methodological materials, monographs, and regulatory documents. The collections cover a wide range of fields: from aerospace technologies, engine engineering, and computer science to history, linguistics, mathematics, and ecology. The archive brings together the scientific heritage of the university, including materials prepared during the period of Samara State Aerospace University and Samara State University.
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| Title: | Проектирование экспериментальной установки для проверки мероприятий по повышению КПД турбин ГТД |
| Authors: | Попов Д. А. Самохвалов Н. Ю. |
| Keywords: | experimental setups gas dynamic modeling gas turbine engines high pressure turbines radial clearances rotor blades semi-naturalistic tests turbine stages газодинамическое моделирование газотурбинные двигатели полунатурные испытания рабочие лопатки радиальные зазоры турбинные ступени турбины высокого давления экспериментальные установки |
| Issue Date: | 2025 |
| Citation: | Попов, Д. А. Проектирование экспериментальной установки для проверки мероприятий по повышению КПД турбин ГТД = Design of an experimental test rig for checking constructive methods for increasing the efficiency of GTE turbines / Д. А. Попов, Н. Ю. Самохвалов // Перспективы развития двигателестроения : материалы междунар. науч.-техн. конф. им. Н. Д. Кузнецова (18–20 июня 2025 г.) / Самар. нац. исслед. ун-т им. С. П. Королева (Самар. ун-т) ; редкол.: Е. В. Шахматов, А. И. Ермаков. - Самара : Изд-во Самар. ун-та, 2025. - С. 844-846. |
| Abstract: | Numerical simulation was chosen as a research method. Computational model has been verified and configured based on the results of previous tests. The results of numerical modeling showed that the proposed design of the rotor blade tip squealer allows to reduce the kinetic energy losses in the rotor blade by more than 11 % (rel.), increasing the efficiency of the high pressure turbine stage by more than 0,27 % (abs.). The positive effect was achieved by changing the structure of secondary vortex structures, dividing large and intense vortex into small ones with lower intensity. |
| URI: | http://repo.ssau.ru/jspui/handle/123456789/43499 |
| Appears in Collections: | Перспективы развития двигателестроения |
| File | Size | Format | |
|---|---|---|---|
| 978-5-7883-2191-2_2025-844-846.pdf | 275 kB | Adobe PDF | View/Open |
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