scholarly journals Experimental and Numerical Investigation of Flow Phenomena in Nonisothermal, Variably Saturated Bentonite–Crushed Rock Mixtures

2003 ◽  
Vol 2 (2) ◽  
pp. 239 ◽  
Author(s):  
Irina Engelhardt ◽  
Stefan Finsterle ◽  
Cor Hofstee
Keyword(s):  
Numerical Investigation ◽  
Crushed Rock ◽  
Flow Phenomena

Numerical investigation of 3-D flow phenomena in interblade channel with tie-boss

2021 ◽  
Author(s):  
Tomáš Radnic ◽  
Jindřich Hála ◽  
Martin Luxa ◽  
Šimurda David
Keyword(s):  
Numerical Investigation ◽  
Flow Phenomena

Experimental and Numerical Investigation of Tip Clearance and Bleed Effects in a Centrifugal Compressor Stage With Pipe Diffuser

2012 ◽  
Vol 135 (1) ◽  
Author(s):  
Robert Kunte ◽  
Philipp Schwarz ◽  
Benjamin Wilkosz ◽  
Peter Jeschke ◽  
Caitlin Smythe
Keyword(s):  
Numerical Investigation ◽  
Centrifugal Compressor ◽  
Tip Clearance ◽  
Compressor Stage ◽  
Local Flow ◽  
Centrifugal Compressor Stage ◽  
Centrifugal Stage ◽  
Flow Phenomena ◽  
Fundamental Insight ◽  
The Impact

The subject of this paper is the experimental and numerical investigation of a state-of-the-art high pressure centrifugal compressor stage with pipe diffuser for a jet engine application. This study shows the impact of impeller tip clearance- and bleed-variation on the centrifugal stage. The purpose of this paper is threefold. In the first place, it investigates the effects on the stage performance. Secondly, it seeks to explain local flow-phenomena, especially in the diffuser. Finally, it shows that steady CFD simulations are capable of predicting these phenomena. Experimental data were gathered using conventional pitot and three-hole-probes as well as particle-image-velocimetry. Numerical simulations with the CFD solver TRACE were conducted to get fundamental insight into the flow. Thus, this study contributes greatly towards understanding the principle of the flow phenomena in the pipe diffuser of a centrifugal compressor.

Numerical Investigation of Axial Compressor Stages With Differing Degrees of Reaction

2014 ◽  
Author(s):  
Jens Ortmanns
Keyword(s):  
Numerical Investigation ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Pressure Rise ◽  
Wall Region ◽  
Compressor Stage ◽  
Tip Leakage Flow ◽  
Degree Of Reaction ◽  
Multi Stage ◽  
Flow Phenomena

In order to increase the efficiency of a compressor module, several loss sources such as aerofoil profile loss, secondary loss and clearance flow phenomena must be taken into account and balanced in the most efficient way. This current document presents the results of a numerical investigation based on a conventionally loaded high pressure compressor stage with different inlet and exit swirls. The effects of changing the degree of reaction on the compressor stage flow pattern is analysed in detail. In general, the correlation between the overall stage efficiency at constant pressure ratio and the degree of stage reaction is low. Nevertheless, the results show a direct impact on the rotor tip leakage flow and the secondary flow phenomena in the stator end-wall region when the degree of reaction is modified which is driven by the change in static pressure rise between the rotor and the stator passages. The balance of these two loss sources might have an impact on the efficiency and the stall behaviour of a multi-stage compressor.

Experimental and Numerical Investigation of the Flow Inside the Return Channel of a Centrifugal Process Compressor

2016 ◽  
Vol 138 (10) ◽  
Author(s):  
C. Rube ◽  
T. Rossbach ◽  
M. Wedeking ◽  
D. R. Grates ◽  
P. Jeschke
Keyword(s):  
Numerical Simulations ◽  
Numerical Investigation ◽  
High Flow ◽  
Performance Data ◽  
Pressure Measurements ◽  
Vaneless Diffuser ◽  
Numerical Predictions ◽  
Flow Phenomena ◽  
Centrifugal Process ◽  
Return Channel

This paper presents the first detailed experimental performance data for a new centrifugal process compressor test rig. Additional numerical simulations supported by extensive pressure measurements at various positions allow an analysis of the operational and loss behavior of the entire stage and its components. The stage investigated is a high flow rate stage of a single-shaft, multistage compressor for industrial applications and consists of a shrouded impeller, a vaneless diffuser, a U-bend, and an adjoining vaned return channel. Large channel heights due to high flow rates induce the formation of highly three-dimensional flow phenomena and thus enlarge the losses due to secondary flows. An accurate prediction of this loss behavior by means of numerical investigations is challenging. The published experimental data offer the opportunity to validate the used numerical methods at discrete measurement planes, which strengthens confidence in the numerical predictions. CFD simulations of the stage are initially validated with global performance data and extensive static pressure measurements in the vaneless diffuser. The comparison of the pressure rise and an estimation of the loss behavior inside the vaneless diffuser provide the basis for a numerical investigation of the flow phenomena in the U-bend and the vaned return channel. The flow acceleration in the U-bend is further assessed via the measured two-dimensional pressure field on the hub wall. The upstream potential field of the return channel vanes allows an evaluation of the resulting flow angle. Measurements within the return channel provide information about the deceleration and turning of the flow. In combination with the numerical simulations, loss mechanisms can be identified and are presented in detail in this paper.

Experimental and Numerical Investigation of Three-Dimensional Viscous Flows and Vortex Motion Inside an Annular Compressor Blade Row

1991 ◽  
Vol 113 (2) ◽  
pp. 198-206 ◽  
Author(s):  
H. E. Gallus ◽  
C. Hah ◽  
H. D. Schulz
Keyword(s):  
Numerical Investigation ◽  
Vortex Motion ◽  
Three Dimensional ◽  
Secondary Flows ◽  
Compressor Cascade ◽  
Complex Flow ◽  
Three Dimensional Flow ◽  
Navier Stokes Equation ◽  
Dimensional Flow ◽  
Flow Phenomena

A detailed experimental and numerical investigation was carried out to examine the three-dimensional flow field, secondary flows, and vortex motion in an annular compressor cascade. Various flow visualizations near the blade surface and endwalls, wall static pressure and loss measurements, as well as hot-film and hot-wire measurements inside the blade boundary layers were performed at various flow rates to understand the complex flow phenomena. A Reynolds-averaged Navier–Stokes equation was solved to investigate the flow numerically. The detailed comparison between measurement and numerical prediction indicates that the complex three-dimensional flow phenomena (corner stall, vortex motion, radial mixing, etc.) are very well predicted with the numerical method.

scholarly journals Numerical Investigation of Cross Flow Phenomena in a Tight-Lattice Rod Bundle Using Advanced Interface Tracking Method

2008 ◽  
Vol 2 (2) ◽  
pp. 456-466 ◽  
Author(s):  
Weizhong ZHANG ◽  
Hiroyuki YOSHIDA ◽  
Yasuo OSE ◽  
Akira OHNUKI ◽  
Hajime AKIMOTO ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Cross Flow ◽  
Interface Tracking ◽  
Tracking Method ◽  
Rod Bundle ◽  
Flow Phenomena ◽  
Tight Lattice
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