Reynolds Number Effects on the Flow through a Savonius Wind Rotor

2021 ◽  
pp. 50-61
Author(s):  
Florian Fruth ◽  
Peter Jeschke ◽  
Holger Franz

A centrifugal compressor has been evaluated numerically for the scalability of aeroelastic parameters for different pressure levels. By maintaining the flow coefficient, as done in the development process, comparable aerodynamics for the compressor cases have been generated ranging from 0.96 bar to 40 bar inlet pressure. It has been found, that the mean static pressure as well as the aerodynamic damping can be scaled by the inlet density ratio. The gained results proofed for this case to be sufficient in magnitude and distribution for an early development stage. Harmonic pressure scaling for centrifugal compressors however has resulted in non-negligible errors. The origin of changes for the setup presented is found in the variation of Reynolds number. Especially the hub and tip sections are influenced and therefore also the secondary flow through the impeller tip gap. This generally results in lower scalability after the transition from axial to radial flow. Hence impeller trailing edge mode shapes have to be considered carefully. The Reynolds number effects become smaller however for higher temperature levels, reducing the scaling errors.


AIAA Journal ◽  
1977 ◽  
Vol 15 (8) ◽  
pp. 1152-1158 ◽  
Author(s):  
C. C. Horstman ◽  
G. S. Settles ◽  
I. E. Vas ◽  
S. M. Bogdonoff ◽  
C.M. Hung

PAMM ◽  
2015 ◽  
Vol 15 (1) ◽  
pp. 489-490
Author(s):  
Davide Modesti ◽  
Matteo Bernardini ◽  
Sergio Pirozzoli

1989 ◽  
Vol 111 (4) ◽  
pp. 464-471 ◽  
Author(s):  
M. Stieglmeier ◽  
C. Tropea ◽  
N. Weiser ◽  
W. Nitsche

This study examines the flow field in three axisymmetric expansions having diffuser half-angles of 14, 18, and 90 deg, respectively. Velocity measurements were performed at a Reynolds number of Re = 1.56 × 104 using a single component LDA operated in forward scatter. The test facility was refractive index matched, allowing measurement of the velocities U, V, W, u2, v2, w2, uv and uw upstream of, and throughout the entire recirculation region. The results indicate that the diffuser geometry influences the separated shear layer appreciably over the entire length of the diffuser section. The production of turbulence immediately after separation is much higher in the case of the 14 and 18 deg diffuser compared to the 90 deg expansion, leading to higher diffusion rates in the separated shear layer, and hence earlier reattachment of the shear layer.


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