scholarly journals Flow Simulation And Performance Analysis Of Centrifugal Compressor Using Cfd_Tool

2021 ◽  
Vol 23 (11) ◽  
pp. 693-703
Author(s):  
Tesfaye Barza ◽  
◽  
G. Lakshmikanth ◽  
Keyword(s):  
Performance Analysis ◽  
Pressure Distribution ◽  
Turbulence Model ◽  
Centrifugal Compressor ◽  
Flow Simulation ◽  
Internal Flow ◽  
Design System ◽  
Turbulent Fluid Flow ◽  
Compressor Impeller ◽  
And Performance

This paper is concerned the flow simulation and performance analysis of the Centrifugal Compressor Using CFD – Tool. The complex internal flow of centrifugal compressor can be well analyzed, and the unique design system needs to be developed. It should be early to use the interface and also flexible for input and output. A 3-D flow simulation of turbulent – fluid flow is presented to visualize the flow pattern in-terms of velocity, streamline and pressure distribution on the blade surface are graphically interpreted. The standard K- e turbulence model and the simple model algorithm were chosen for turbulence model and pressure distribution well determined. The simulation was steady Heat transfer and moving reference frame was used to consider the impeller interaction under high resolution. Furthermore, A computational Fluid Dynamics (CFD) 3-D simulation is done to analyze the impeller head and efficiency required of centrifugal compressor. The impeller is rotated for a constant revolution and mass flow rate, in this study initially the geometry of centrifugal compressor impeller is created by an ANSYS Vista CCD, and the Blade modeller done by Bladegen, Finally, CFD analysis was performed in ANSYS CFX using the ANSYS Turbo grid meshing tool. According to the analysis, as the number of impeller blades increases, so does the value of the head and power imparted, as well as the impeller’s efficiency.

scholarly journals Flow simulation and performance analysis of a drilling turbine

2020 ◽  
Vol 8 (3) ◽  
pp. 255-270
Author(s):  
Khaled Sahnoune ◽  
◽  
Abderrahmane Benbrik ◽  
Rekik Oussama ◽  
Ahmed S. Mansour ◽  
...  
Keyword(s):  
Performance Analysis ◽  
Flow Simulation ◽  
And Performance

Internal flow simulation of high-performance solid rockets using a k-ω turbulence model

2005 ◽  
Vol 14 (2) ◽  
pp. 114-119 ◽  
Author(s):  
V. R. Sanal Kumar ◽  
H. D. Kim ◽  
B. N. Raghunandan ◽  
T. Setoguchi ◽  
S. Raghunathan
Keyword(s):  
Turbulence Model ◽  
High Performance ◽  
Flow Simulation ◽  
Internal Flow ◽  
Solid Rockets

Unsteady and Three-Dimensional Flow Phenomena in a Transonic Centrifugal Compressor Impeller at Rotating Stall

2009 ◽  
Author(s):  
Kenichiro Iwakiri ◽  
Masato Furukawa ◽  
Seiichi Ibaraki ◽  
Isao Tomita
Keyword(s):  
Centrifugal Compressor ◽  
Wavelet Transforms ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Internal Flow ◽  
Leading Edge ◽  
Rotating Stall ◽  
Detached Eddy Simulation ◽  
Transonic Centrifugal Compressor ◽  
Compressor Impeller

This paper presents a combined experimental and numerical analysis of rotating stall in a transonic centrifugal compressor impeller for automotive turbochargers. Stall characteristics of the compressor were examined by two high-response pressure transducers mounted on the casing wall near the impeller inlet. The pressure traces were analyzed by wavelet transforms to estimate the disturbance waves quantitatively. Three-dimensional unsteady internal flow fields were simulated numerically by Detached Eddy Simulation (DES) coupled LES-RANS approach. The analysis results show good agreements on both compressor performance characteristics and the unsteady flow features at the rotating stall. At stall inception, spiral-type breakdown of the full-blade tip leakage vortex was found out at some passages and the brokendown regions propagated against the impeller rotation. This phenomenon changed with throttling, and tornado-type separation vortex caused by the full-blade leading edge separation dominated the flow field at developed stall condition. It is similar to the flow model of short-length scale rotating stall established in an axial compressor rotor.

Investigation of a Centrifugal Compressor Stage With Two Volutes and the Same Impeller

2003 ◽  
Author(s):  
Yinghui Dai ◽  
Abraham Engeda ◽  
Michael Cave ◽  
Jean-Luc Di Liberti
Keyword(s):  
Experimental Data ◽  
Numerical Simulation ◽  
Centrifugal Compressor ◽  
Internal Flow ◽  
Sudden Expansion ◽  
Compressor Stage ◽  
Centrifugal Compressor Stage ◽  
Compressor Impeller ◽  
Overall Performance ◽  
Good Agreement

Volute scroll, conic diffuser and sudden expansion discharge loss account for 4–6 points of efficiency decrement in a typical centrifugal compressor stage. The flow in a volute is highly complex. It is strongly believed that understanding of the detailed flow structure in a volute will provide insights on minimizing the losses by isolating the mechanisms that contributes to entropy generation. The result will be a more efficient centrifugal compressor product for customers and users and a product at higher profitability levels for manufacturers. This paper presents the experimental and numerical investigation on the matching of two different overhung volutes to the same centrifugal compressor impeller. The experimental data were measured from flange to flange firstly, then three Kiel probes were installed on pinch position circumferentially. At the same time, a detailed numerical simulation of the performance of the two volutes has been carried out. A computational model, using the k-ε turbulence model and the wall function, has been used to predict the internal flow of the both volutes. A good agreement between experimental data and numerical simulation results is found. The overall performance of the two volutes was also discussed in detail.

Numerical study on the Effect of Interaction Vaned Diffuser with Impeller on the Performance of a Modified Centrifugal Compressor

2013 ◽  
Vol 30 (2) ◽  
pp. 113-121 ◽  
Author(s):  
L. H. Jawad ◽  
S. Abdullah ◽  
R. Zulkifli ◽  
W. M. F. W. Mahmood
Keyword(s):  
Centrifugal Compressor ◽  
Numerical Study ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Internal Flow ◽  
Compressor Stage ◽  
Vaned Diffuser ◽  
Centrifugal Compressor Stage ◽  
Compressor Impeller ◽  
Inlet Conditions

ABSTRACTThis paper is a numerical simulation that was made in the three-dimensional flow, carried out in a modified centrifugal compressor, having vaned diffuser stage, used as an auto-motive turbo charger. Moreover, the performance of the centrifugal compressor was dependent on the proper matching between compressor impeller and vaned diffuser, influencing significantly surge and the efficiency of centrifugal compressor stages. In addition, a modified compressor impeller, coupled with vane and vaneless diffuser, has been found to have similar internal flow patterns for both the vaneless and vaned diffuser design. The vaned diffuser effect has been paid particular attention in terms of better analysis where the diffuser was designed for high sub-sonic inlet conditions. Another aim of this research was to study and simulate the effect of vaned diffuser on the performance of a centrifugal compressor. The simulation was undertaken by using a commercial software, the so-called ANSYS CFX, to predict numerically the performance in terms of pressure ratio, poly tropic efficiency and mass flow rate for the centrifugal compressor stage. The results were generated from CFD and were analyzed for better understanding of the fluid flow through centrifugal compressor stage. Conclusively, it was observed that the effect of the vaned diffuser is to convert the kinetic energy into a high static pressure after analyzing the results of the simulation.

Numerical Investigation on the Formation of Jet-Wake Flow Pattern in Centrifugal Compressor Impeller

2003 ◽  
Author(s):  
Qun Zheng ◽  
Shunlong Liu
Keyword(s):  
Pattern Formation ◽  
Flow Field ◽  
Numerical Investigation ◽  
Centrifugal Compressor ◽  
Internal Flow ◽  
Secondary Flows ◽  
Wake Flow ◽  
Centrifugal Impeller ◽  
Numerical Investigations ◽  
Compressor Impeller

Numerical investigations of internal flow field in centrifugal compressor impeller channel are carried out in this paper. Topological analyses of limit streamline pattern are used to interpret the Jet-Wake formation. With such a technique, it can give a clearly description of the wake. And the shape of the wake, the wake onset and wake developing process are depicted in detail. The numerical results also present the internal vortices, secondary flows and their effects on the Jet-Wake pattern formation. The influences of Coriolis force on flow field of the centrifugal impeller are also discussed.

Effect of Tip Clearance on the Flow and Performance of a Centrifugal Compressor

2003 ◽  
Author(s):  
Soon-Sam Hong ◽  
Matthias Schleer ◽  
Reza S. Abhari
Keyword(s):  
Centrifugal Compressor ◽  
Fast Response ◽  
Tip Clearance ◽  
Wake Region ◽  
Clearance Ratio ◽  
Flow Measurements ◽  
Time Resolved ◽  
Compressor Impeller ◽  
Blade Tip ◽  
And Performance

To see the tip clearance effect on a centrifugal compressor, time-resolved flow measurements were carried out at the discharge of a centrifugal compressor impeller, which is 30 deg back swept from radial and operated at the blade tip speed of 260 m/s. Tested were six cases of tip clearance ratio ranged from 0.06 to 0.21. A fast response aerodynamic probe equipped with a single pressure sensor was used for the flow measurements. From the distribution of time-resolved relative velocity, the jet-wake structure was observed. The wake downstream of the splitter blade was located in the shroud-suction corner, but that downstream of the full blade was in the mid-shroud. By increasing the tip clearance, the wake region was increased and the deficit of the relative total pressure governed the wake region, therefore, the loss was enlarged.

Compressor Volute Design System: Part I — Volute Design by Bezier Application

2002 ◽  
Author(s):  
Guy Phuong ◽  
Sylvester Abanteriba ◽  
Paul Haley
Keyword(s):  
System Approach ◽  
Three Dimensional ◽  
Flow Simulation ◽  
Design System ◽  
Centrifugal Compressors ◽  
Output Data ◽  
B Spline ◽  
Actual Design ◽  
System Part ◽  
And Performance

This is Part I of a two-part paper describing a new compressor volute design system, which is applied to an interactive program that completely describes volute geometry and its interactions with CFD. Part I goes into the theory behind the program and the design of the volute geometry by application of Bezier polynomials while Part II fully describes the actual design system approach and its application to the program. Based on the developed mathematics of B-spline and Bezier polynomials, the present paper further develops the extent of Bezier polynomials by application of Bezier to volute design. Bezier polynomials will be used to describe and define volute geometry for centrifugal compressors with the objective of serving as an aid for volute design and performance analysis. The current research aims to develop an algorithm for volute design that will enable the volute geometry, to be fully described and viewed, in two-dimensional (2D) and three-dimensional (3D) modes. A program based on this algorithm will deliver output data for grid generation and CFD flow simulation and eventual manufacture of the volute. These procedures will be developed for a family of centrifugal compressors.

A Novel Quasi 3-D Design Method for Centrifugal Compressor Meridional Plane

2010 ◽  
Author(s):  
Mahdi Nili-Ahmadabadi ◽  
Mohammad Durali ◽  
Ali Hajilouy-Benisi
Keyword(s):  
Pressure Distribution ◽  
Centrifugal Compressor ◽  
Design Method ◽  
Navier Stokes ◽  
Meridional Plane ◽  
3D Analysis ◽  
3D Design ◽  
Design Algorithm ◽  
Compressor Impeller ◽  
The Difference

This paper is concerned with a quasi-3D design method for centrifugal compressor impeller in the meridional plane. The method links up a novel inverse design algorithm, called Ball-Spine Algorithm (BSA), and a quasi-3D analysis code. The Euler equation is solved on the meridional plane for a numerical domain of which some unknown boundaries (hub and shroud) are iteratively modified under the BSA until a prescribed pressure distribution is reached. In BSA, the unknown walls are composed of a set of virtual balls that move freely along the specified directions called spines. The difference between target and current pressure distribution causes to deform flexible boundary at each modification step. In order to validate the quasi-3D analysis code, an existing compressor is investigated by some experiments in which several static pressure points on the shroud, the flow parameters at the compressor inlet and outlet are measured. Comparison of the quasi-3D analysis results with experimental results shows good agreement. Also, a full 3D Navier-Stokes code is used to analyze the existing and designed compressor numerically. The results show that the momentum decrease near the shroud wall in the existing compressor is removed by hub-shroud modification resulting an improvement in performance by 0.6 percent.

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