Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls
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...
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MDPI AG
2024-11-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/11/11/946 |
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| author | Valeriu Drăgan Oana Dumitrescu Mihnea Gall Emilia Georgiana Prisăcariu Bogdan Gherman |
| author_facet | Valeriu Drăgan Oana Dumitrescu Mihnea Gall Emilia Georgiana Prisăcariu Bogdan Gherman |
| author_sort | Valeriu Drăgan |
| collection | DOAJ |
| description | 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. |
| format | Article |
| id | doaj-art-6325c56e3b054f089e264510da28f96f |
| institution | OA Journals |
| issn | 2226-4310 |
| language | English |
| publishDate | 2024-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj-art-6325c56e3b054f089e264510da28f96f2025-08-20T02:26:50ZengMDPI AGAerospace2226-43102024-11-01111194610.3390/aerospace11110946Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous WallsValeriu Drăgan0Oana Dumitrescu1Mihnea Gall2Emilia Georgiana Prisăcariu3Bogdan Gherman4Romanian Research and Development Institute for Gas Turbines COMOTI, 061126 Bucharest, RomaniaRomanian Research and Development Institute for Gas Turbines COMOTI, 061126 Bucharest, RomaniaRomanian Research and Development Institute for Gas Turbines COMOTI, 061126 Bucharest, RomaniaRomanian Research and Development Institute for Gas Turbines COMOTI, 061126 Bucharest, RomaniaRomanian Research and Development Institute for Gas Turbines COMOTI, 061126 Bucharest, RomaniaTurbomachinery 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.https://www.mdpi.com/2226-4310/11/11/946turbomachinerypressure wavesmicroperforated wallpassive controlschlieren visualization |
| spellingShingle | Valeriu Drăgan Oana Dumitrescu Mihnea Gall Emilia Georgiana Prisăcariu Bogdan Gherman Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls Aerospace turbomachinery pressure waves microperforated wall passive control schlieren visualization |
| title | Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls |
| title_full | Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls |
| title_fullStr | Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls |
| title_full_unstemmed | Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls |
| title_short | Experimental Identification of a New Secondary Wave Pattern in Transonic Cascades with Porous Walls |
| title_sort | experimental identification of a new secondary wave pattern in transonic cascades with porous walls |
| topic | turbomachinery pressure waves microperforated wall passive control schlieren visualization |
| url | https://www.mdpi.com/2226-4310/11/11/946 |
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