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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Bibliographic Details
Published in:Aerospace 2024-11, Vol.11 (11), p.946
Main Authors: Drăgan, Valeriu, Dumitrescu, Oana, Gall, Mihnea, Prisăcariu, Emilia Georgiana, Gherman, Bogdan
Format: Article
Language:English
Subjects:
Air flow
Blades
Boundary layers
Cascades (Fluid dynamics)
Design
Design and construction
Dissipation
Efficiency
Elastic waves
Flow rates
Manufacturing
Methods
microperforated wall
Numerical methods
passive control
Porous walls
Pressure distribution
Pressure variations
pressure waves
Reynolds averaged Navier-Stokes method
schlieren visualization
Shock waves
Turbomachinery
Turbomachines
Turbulence models
Ventilation
Visualization
Citations: Items that this one cites
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Summary: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.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace11110946