| Autor: |
Valeriu Drăgan, Oana Dumitrescu, Mihnea Gall, Emilia Georgiana Prisăcariu, Bogdan Gherman |
| Jazyk: |
angličtina |
| Rok vydání: |
2024 |
| Předmět: |
|
| Zdroj: |
Aerospace, Vol 11, Iss 11, p 946 (2024) |
| Druh dokumentu: |
article |
| ISSN: |
2226-4310 |
| DOI: |
10.3390/aerospace11110946 |
| Popis: |
Turbomachinery shock wave patterns occur as a natural result of operating at off-design points and are accountable for some of the loss in performance. In some cases, shock wave–boundary layer (SW-BLIs) interactions may even lead to map restrictions. The current paper refers to experimental findings on a transonic linear cascade specifically designed to mitigate shock waves using porous walls on the blades. Schlieren visualization reveals two phenomena: Firstly, the shock waves were dissipated in all bladed passages, as predicted by the CFD studies. Secondly, a lower-pressure wave pattern was observed upstream of the blades. It is this phenomenon that the paper reports and attempts to describe. Attempts to replicate this pattern using Reynolds-averaged Navier–Stokes (RANS) calculations indicate that the numerical method may be too dissipative to accurately capture it. The experimental campaign demonstrated a 4% increase in flow rate, accompanied by minimal variations in pressure and temperature, highlighting the potential of this approach for enhancing turbomachinery performance. |
| Databáze: |
Directory of Open Access Journals |
| Externí odkaz: |
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