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Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls
- Source :
- Aerospace, Vol 11, Iss 11, p 946 (2024)
- Publication Year :
- 2024
- Publisher :
- MDPI AG, 2024.
-
Abstract
- 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.
Details
- Language :
- English
- ISSN :
- 22264310
- Volume :
- 11
- Issue :
- 11
- Database :
- Directory of Open Access Journals
- Journal :
- Aerospace
- Publication Type :
- Academic Journal
- Accession number :
- edsdoj.6325c56e3b054f089e264510da28f96f
- Document Type :
- article
- Full Text :
- https://doi.org/10.3390/aerospace11110946