scholarly journals Analysis and Optimization of the Performances of the Centrifugal Compressor Using the CFD

2021 ◽  
Vol 39 (1) ◽  
pp. 107-120
Author(s):  
Brihmat Mostefa ◽  
Refassi Kaddour ◽  
Douroum Embarek ◽  
Kouadri Amar
Keyword(s):  
Centrifugal Compressor ◽  
Internal Flow ◽  
Design Tool ◽  
Design System ◽  
Optimization Approach ◽  
Original Design ◽  
Predicting Performance ◽  
Compressor Design ◽  
Current Design ◽  
Compressor Performance

Centrifugal compressors have been used in many areas of the machinery. The centrifugal compressor design is very complex, and a unique design system needs to be developed. A centrifugal compressor design system should be easy to use in interface and also flexible for inputs and outputs. The design tool also needs to be able to predicate the compressor performance in a fairly accurate level. In this study, we have developed a general analyses and optimization approach in the design and performance analysis of centrifugal turbomachines. This approach is based on different methods starting from a 1D approach up to the 3D study of the internal flow. It presents itself as a robust procedure for predicting and understanding the phenomena associated with the operation of turbomachines, but also for predicting performance. Current design system includes initial parameter studies, throughflow calculation, impeller design. The main improvements of the design system are adding the interface to allow users easy to use, adding the input and output capabilities and modifying few correlations. Current design system can predict the blade loading and compressor performance better compared with original design system. To check the aerodynamic appearance of the centrifugal compressor impeller blades, we must change the impeller dimensions and focus on changing axial length, but when changing the blade numbers, the model that improved efficiency and power at the same time introduced a design with a 0.274% and 10.735% improvement in each respectively in comparison to the initial impeller at the design point.

Aerodynamic and Structure Considerations in Centrifugal Compressor Design: Blade Lean Effects

2012 ◽  
Author(s):  
C. Xu ◽  
R. S. Amano
Keyword(s):  
Centrifugal Compressor ◽  
Structural Reliability ◽  
Three Dimensional ◽  
Design System ◽  
Compressor Wheel ◽  
Through Flow ◽  
Compressor Design ◽  
Recent Developments ◽  
Compressor Performance ◽  
Wide Operating

Optimization procedures are demanded by turbomachinery industries that enable to enhance compressor efficiency and wide operating ranges. Most of the design processes focuseither on aerodynamics or structure. However, the compressor design is an integration between aerodynamics and structure. This paper presents some recent developments of the aerodynamic and structural integral design system. The design process including the meanline design, through-flow optimization and three-dimensional viscous analysis was used in the centrifugal compressor design. The aerodynamic and structural design need to be optimized at the same time. Normally most of the favorable aerodynamic features do not correspond with the structural reliability of the compressor wheel. The optimization between aerodynamic performance and structural reliability is critical to provide the maximal potential of the compressor performance. The main purpose of the current study is to discuss the importance of the aerodynamic and structural optimizations through a centrifugal compressor wheel lean effects. The study demonstrated that the integral design of the aerodynamics and structure is very important.

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 Experience With an Integrated Centrifugal Compressor Design Procedure

1984 ◽  
Author(s):  
Gregory J. Holbrook ◽  
Joost J. Brasz
Keyword(s):  
Centrifugal Compressor ◽  
Integrated Design ◽  
Design Procedure ◽  
Internal Flow ◽  
Two Dimensional ◽  
One Dimensional ◽  
Flow Models ◽  
Compressor Design ◽  
Design Case Study ◽  
The One

An integrated centrifugal compressor design procedure is described consisting of several phases, each using progressively more complex models. After initially sizing the compressor overall geometry, the detailed geometry is first determined from a one-dimensional mean streamline model. This geometry is subsequently analyzed by more complex two-dimensional hub-to-shroud and blade-to-blade internal flow models. The one-dimensional mean streamline model is a key element in this integrated design procedure, since it links the results of the preliminary sizing model with the more sophisticated two-dimensional internal flow models. It quickly determines a complete (hub and shroud contour and blade angle distributions) compressor geometry from a desired blade loading distribution and the overall performance requirements of the compressor. After a presentation of this mean streamline design model and its assumptions, an impeller design case study is given using the integrated centrifugal compressor design procedure. From a comparison between the actual flow predictions of the various models it can be concluded that the major aerodynamic trends are properly described by the mean streamline model.

scholarly journals Experimental Study on Effects of Adjustable Vaned Diffusers on Impeller Backside Cavity of Centrifugal Compressor in CAES

Energies ◽  
2021 ◽  
Vol 14 (19) ◽  
pp. 6187
Author(s):  
Zhihua Lin ◽  
Zhitao Zuo ◽  
Wenbin Guo ◽  
Jianting Sun ◽  
Qi Liang ◽  
...  
Keyword(s):  
Centrifugal Compressor ◽  
Static Pressure ◽  
Internal Flow ◽  
Operating Conditions ◽  
Test Facility ◽  
Angle Change ◽  
Temperature Loss ◽  
Impeller Outlet ◽  
Compressor Performance ◽  
Variable Operating Conditions

The impeller backside cavity (IBC) is a unique structure of centrifugal compressor in compressed air energy storage (CAES) systems, which affects the aerodynamic performance of centrifugal compressor, and the angle change of the downstream coupled adjustable vaned diffusers (AVDs) will affect the flow field inside the cavity and compressor performance. This paper relies on the closed test facility of the high-power intercooling compressor to measure static pressure and static temperature at different radii on the static wall of the IBC. The coupling relationship between the IBC and compressor under variable operating conditions is analyzed, and the influence of AVDs on the internal flow in IBC is studied. The results show that static pressure and static temperature rise along the direction of increasing radius, but static temperature drops near the coupling between the impeller outlet and the cavity inlet. Under AVDs’ design angle, static pressure and static temperature at each point, static pressure loss and static temperature loss in the direction of decreasing radius all increase as the flow decreases. Under variable AVDs’ angles, static pressure and static temperature will change differently, and respective loss will also be different.

Prediction of Centrifugal Compressor Performance From Choke Through Stall With a Physical Throttle

2015 ◽  
Author(s):  
Xiaocheng Zhu ◽  
Kai Jia ◽  
Zhaohui Du
Keyword(s):  
Unsteady Flow ◽  
Centrifugal Compressor ◽  
Three Dimensional ◽  
Internal Flow ◽  
Ambient Conditions ◽  
Vaneless Diffuser ◽  
Flow Physics ◽  
Flow Simulations ◽  
Performance Curves ◽  
Compressor Performance

Numerical simulation results of the internal flow field of a centrifugal compressor with vaneless diffuser are presented by solving three-dimensional Reynolds averaged compressible NS equations using CFD software CFX. A physical throttle added at the downstream of the volute has been successful in stabilizing the flow at all flow rates. Ambient conditions are held fixed at both the inlet and exit of the domain. Numerical results of an investigation in which the predicted aerodynamic performance of the centrifugal compressor with vaneless diffuser is compared with the measured experimental data over the entire design speedline from choke through stall are presented. Performance curves of different components are also presented. A physical throttle approach for the prediction of the unsteady flow physics that lead to stall is proposed and a series of unsteady-flow simulations are used to illustrate the instability flow physics in the impeller, the vaneless diffuser and the volute.

One-Dimensional Preliminary Centrifugal Compressor Design Tool for Undergraduate Courses

2020 ◽  
Author(s):  
Daniel da Silva Tonon ◽  
George Guimarães Dias Siqueira ◽  
Jesuino Takachi Tomita ◽  
Cleverson Bringhenti
Keyword(s):  
Centrifugal Compressor ◽  
Design Tool ◽  
One Dimensional ◽  
Compressor Design

Aerodynamic Analysis in Lean Blade Effects in Centrifugal Compressor

2011 ◽  
Author(s):  
Cheng Xu ◽  
R. S. Amano ◽  
A. Alkhalidi
Keyword(s):  
Centrifugal Compressor ◽  
Three Dimensional ◽  
Design System ◽  
Aerodynamic Optimization ◽  
Compressor Wheel ◽  
Structure Reliability ◽  
System A ◽  
Compressor Design ◽  
Recent Developments ◽  
Wide Operating

Turbomachinery industries are interested in using optimization procedures that enable to enhance compressor efficiency and wide operating ranges. Most of the design processes are focus on either in aerodynamics or structure. However, the compressor design is an integration between the aerodynamics and structure. This paper presents the recent developments of the aerodynamic integral design system. A design process including the meanline design, throughflow optimization and three-dimensional viscous analysis was used in the centrifugal compressor design. The aerodynamic design design needs to optimize at same time. Normally the most of performance of the favorite features are not friendly to the structure reliability of the compressor wheel. The optimization between aerodynamic performance and structure reliability is critical to provide the maximal potential of the compressor design. The main purpose of current paper is to discuss the importance of the aerodynamic optimization through lean effects. It can be seen from the discussion that the integration of aerodynamics is very important.

scholarly journals Prediction and Evaluation of Waterjet Pump Performance under Nonuniform Inflow Using Parallel Compressor Theory

Water ◽  
2021 ◽  
Vol 13 (1) ◽  
pp. 99
Author(s):  
Puyu Cao ◽  
Rui Zhu
Keyword(s):  
Flow Instability ◽  
Internal Flow ◽  
Weighted Sum ◽  
Pump Performance ◽  
Inlet Velocity ◽  
Inlet Distortion ◽  
Pump Head ◽  
Compressor Performance ◽  
Waterjet Pump ◽  
External Characteristics

Parallel compressor theory (PCT) is commonly used to estimate effects of inlet distortion on compressor performance. As well as compressor, the actual inflow to pump is also nonuniform and unfavorable for performances. Nowadays, insufficient understanding of nonuniform inflow effects on pump performance restricts its development. Therefore, this paper applies PCT to predict external characteristics and evaluate internal flow instability of waterjet pump under nonuniform inflow. According to features of nonuniform inflow, the traditional PCT is modified and makes waterjet pump sub-divided into two circumferential tubes owning same performances but with different inlet velocity (representing nonuniform inflow). Above all, numerical simulation has been conducted to validated the applicability and accuracy of PCT in head prediction of waterjet pump under nonuniform inflow, since area-weighted sum of each tube head (i.e., theoretical pump head) is highly consistent with simulated result. Moreover, based on identifications of when and which tube occurs stall, PCT evaluates four stall behaviors of waterjet pump: partial deep stall, partial stall, pre-stall and full stall. Furthermore, different stall behavior generates different interactions between head variation of each tube, resulting in a multi-segment head curve under nonuniform inflow. The modified PCT with associated physical interpretations are expected to provide a sufficient understanding of nonuniform inflow effects on pump performances.

Effects of Diffuser Vane Geometries on Compressor Performance and Noise Characteristics in a Centrifugal Compressor

2013 ◽  
Author(s):  
Yohei Morita ◽  
Nobumichi Fujisawa ◽  
Takashi Goto ◽  
Yutaka Ohta
Keyword(s):  
Centrifugal Compressor ◽  
Noise Level ◽  
Leading Edge ◽  
Broadband Noise ◽  
Frequency Noise ◽  
Numerical Techniques ◽  
Vaned Diffuser ◽  
Noise Characteristics ◽  
Edge Vortex ◽  
Compressor Performance

The effects of the diffuser vane geometries on the compressor performance and noise characteristics of a centrifugal compressor equipped with vaned diffusers were investigated by experiments and numerical techniques. Because we were focusing attention on the geometries of the diffuser vane’s leading edge, diffuser vanes with various leading edge geometries were installed in a vaned diffuser. A tapered diffuser vane with the tapered portion near the leading edge of the diffuser’s hub-side could remarkably reduce both the discrete frequency noise level and broadband noise level. In particular, a hub-side tapered diffuser vane with a taper on only the hub-side could suppress the development of the leading edge vortex (LEV) near the shroud side of the diffuser vane and effectively enhanced the compressor performance.

Automated Blade Optimization and 3D CFD Analysis for an Axial Multistage GT Compressor Redesign

2006 ◽  
Author(s):  
Lars Moberg ◽  
Gianfranco Guidati ◽  
Sasha Savic
Keyword(s):  
Flow Analysis ◽  
Optimization Methods ◽  
Design System ◽  
Cfd Analysis ◽  
Controlled Diffusion ◽  
Repetitive Tasks ◽  
Blade Optimization ◽  
Through Flow ◽  
Compressor Design ◽  
Linux Cluster

This paper focuses on (1) the basic compressor layout based on meridional through flow analysis and (2) the re-design of blades and vanes using sophisticated automated design optimization methods. All tools and processes are integrated into a consistent Compressor Design System, which runs on a powerful Linux cluster. This design system allows designing, analyzing and documenting blade design in mostly automated way. This frees the engineer from repetitive tasks and allows him to concentrate on a physical understanding and improvement of the compressor. The tools and methods are illustrated on the basis of an actual ALSTOM compressor. The main objectives of this upgrade are a modest increase in mass flow and an efficiency improvement. The latter is to be achieved through the replacement of NACA blades by modern Controlled Diffusion Airfoils (CDA). Results are presented including a CFD analysis of the front stages of the baseline and upgrade compressor.

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