Numerical Evaluation of Flow Fields and Stresses Acting on Agglomerates Dispersed in High-Pressure Microsystems

2012 ◽  
Vol 35 (11) ◽  
pp. 1922-1930 ◽  
Author(s):  
S. Beinert ◽  
T. Gothsch ◽  
A. Kwade
Keyword(s):  
High Pressure ◽  
Numerical Evaluation ◽  
Flow Fields

Flow-Field and Hydromechanics Analysis of High Pressure Water-Jet Single Nozzle in Radial Horizontal Drilling

2014 ◽  
Vol 952 ◽  
pp. 186-189
Author(s):  
Xian Zhong Yi ◽  
Song Lin Yi ◽  
Hui Shu ◽  
Yuan Qiang Ji ◽  
Sheng Zong Jiang
Keyword(s):  
Numerical Simulation ◽  
High Pressure ◽  
Flow Fields ◽  
Rock Breaking ◽  
External Flow ◽  
Water Jet ◽  
Pressure Water ◽  
Jet Nozzle ◽  
High Pressure Water Jet ◽  
Radial Drilling

The technology of high pressure water jet in radial drilling has currently been used widely at home and abroad. A numerical simulation and analysis of the internal and external flow fields of jet nozzle will 1ay the foundation for the further study of high pressure water jet rock breaking. The physical and mathematical models of axial-symmetrical submerged jet rock breaking with single nozzle were established. And a numerical simulation of the internal and external flow fields of high pressure water jet nozzle in radial drilling was conducted with the Fluent software. The 1aws of the internal and external flow fields were analyzed in different jet distances and inlet flow rates.

Numerical evaluation of a PEM fuel cell with conventional flow fields adapted to tubular plates

2014 ◽  
Vol 39 (29) ◽  
pp. 16694-16705 ◽  
Author(s):  
J.M. Sierra ◽  
S.J. Figueroa-Ramírez ◽  
S.E. Díaz ◽  
J. Vargas ◽  
P.J. Sebastian
Keyword(s):  
Fuel Cell ◽  
Numerical Evaluation ◽  
Pem Fuel Cell ◽  
Flow Fields

Aerodynamic Analysis of an Innovative Low Pressure Vane Placed in an s-Shape Duct

2011 ◽  
Vol 134 (1) ◽  
Author(s):  
Sergio Lavagnoli ◽  
Tolga Yasa ◽  
Guillermo Paniagua ◽  
Lionel Castillon ◽  
Simone Duni
Keyword(s):  
High Pressure ◽  
Unsteady Flow ◽  
Pressure Ratio ◽  
Complex Structure ◽  
Leading Edge ◽  
Low Pressure ◽  
Flow Fields ◽  
Strong Impact ◽  
Turbine Stage ◽  
Spectrum Distribution

In this paper the aerodynamics of an innovative multisplitter low pressure (LP) stator downstream of a high pressure turbine stage is presented. The stator row, located inside a swan necked diffuser, is composed of 16 large structural vanes and 48 small airfoils. The experimental characterization of the steady and unsteady flow fields was carried out in a compression tube rig under engine representative conditions. The one-and-a-half turbine stage was tested at three operating regimes by varying the pressure ratio and the rotational speed. Time-averaged and time-accurate surface pressure measurements are used to investigate the aerodynamic performance of the stator and the complex interaction mechanisms with the high pressure (HP) turbine stage. Results show that the strut blade has a strong impact on the steady and unsteady flow fields of the small vanes depending on the vane circumferential position. The time-mean pressure distributions around the airfoils show that the strut influence is significant only in the leading edge region. At off-design condition (higher rotor speed) a wide separated region is present on the strut pressure side and it affects the flow field of the adjacent vanes. A complex behavior of the unsteady surface pressures was observed. Up to four pressure peaks are identified in the time-periodic signals. The frequency analysis also shows a complex structure. The spectrum distribution depends on the vane position. The contribution of the harmonics is often larger than the fundamental frequency. The forces acting on the LP stator vanes are calculated. The results show that higher forces act on the small vanes but largest fluctuations are experienced by the strut. The load on the whole stator decreases 30% as the turbine pressure ratio is reduced by approximately 35%.

Fast numerical evaluation of flow fields with vortex cells

2009 ◽  
Vol 28 (5) ◽  
pp. 660-669 ◽  
Author(s):  
T. Hetsch ◽  
R. Savelsberg ◽  
S.I. Chernyshenko ◽  
I.P. Castro
Keyword(s):  
Numerical Evaluation ◽  
Flow Fields

Investigation of the Flow Field in a High-Pressure Turbine Stage for Two Stator-Rotor Axial Gaps—Part I: Three-Dimensional Time-Averaged Flow Field

2006 ◽  
Vol 129 (3) ◽  
pp. 572-579 ◽  
Author(s):  
P. Gaetani ◽  
G. Persico ◽  
V. Dossena ◽  
C. Osnaghi
Keyword(s):  
High Pressure ◽  
Flow Field ◽  
Three Dimensional ◽  
Flow Fields ◽  
Secondary Flows ◽  
Point Of View ◽  
Flow Structures ◽  
Axial Distance ◽  
Turbine Stage ◽  
High Pressure Turbine

An extensive experimental analysis on the subject of unsteady flow field in high-pressure turbine stages was carried out at the Laboratorio di Fluidodinamica delle Macchine (LFM) of Politecnico di Milano. The research stage represents a typical modern HP gas turbine stage designed by means of three-dimensional (3D) techniques, characterized by a leaned stator and a bowed rotor and operating in high subsonic regime. The first part of the program concerns the analysis of the steady flow field in the stator-rotor axial gap by means of a conventional five-hole probe and a temperature sensor. Measurements were carried out on eight planes located at different axial positions, allowing the complete definition of the three-dimensional flow field both in absolute and relative frame of reference. The evolution of the main flow structures, such as secondary flows and vane wakes, downstream of the stator are here presented and discussed in order to evidence the stator aerodynamic performance and, in particular, the different flow field approaching the rotor blade row for the two axial gaps. This results set will support the discussion of the unsteady stator-rotor effects presented in Part II (Gaetani, P., Persico, G., Dossena, V., and Osnaghi, C., 2007, ASME J. Turbomach., 129(3), pp. 580–590). Furthermore, 3D time-averaged measurements downstream of the rotor were carried out at one axial distance and for two stator-rotor axial gaps. The position of the probe with respect to the stator blades is changed by rotating the stator in circumferential direction, in order to describe possible effects of the nonuniformity of the stator exit flow field downstream of the stage. Both flow fields, measured for the nominal and for a very large stator-rotor axial gap, are discussed, and results show the persistence of some stator flow structures downstream of the rotor, in particular, for the minimum axial gap. Finally, the flow fields are compared to evidence the effect of the stator-rotor axial gap on the stage performance from a time-averaged point of view.

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