Numerical Simulation of Three Dimensional Flow in Large Mixed-Flow Pump System

2011 ◽  
Author(s):  
Fan Yang ◽  
Chao Liu ◽  
Fangping Tang
Keyword(s):  
Pressure Distribution ◽  
Model Test ◽  
Static Pressure ◽  
Three Dimensional ◽  
Mixed Flow ◽  
Three Dimensional Flow ◽  
Pump System ◽  
Static Pressure Distribution ◽  
Calculation Results ◽  
Flow Pump

The three-dimensional flow inside a mixed-flow pump system was simulated by using CFX software. The Shear Stress Transport turbulent equation which combined k-ε and k-ω turbulent model was applied. The flow field in volute and discharge passage of the pump system was obtained and the hydraulic performances of the pump system were predicted. The velocity and pressure distribution in pump system were analyzed. From the calculation results it is evident that the flow in the double helix volute passage is a spiral movement combining axial and rotary flow; the static pressure distribution in the volute is symmetric; the uniformity of axial velocity distribution and velocity-weighted average swirl angle at the outlet section are relatively low; and static pressure distribution on pump blade surface is regular with higher static pressure on pressure side and lower one on the suction side. The axial forces decrease gradually with the decrease of lifting head and the radial forces decrease first and then increase. A model test of the pump system was conducted to verify the calculation results. The pressure fluctuation at certain sections of the pump system was measured from the model test. A good agreement was found for lifting head between calculated and measured results. While the deviation of the efficiency between calculated and measured results does exist in non design points which need to be improved.

Ingestion Into the Upstream Wheelspace of an Axial Turbine Stage

1994 ◽  
Vol 116 (2) ◽  
pp. 327-332 ◽  
Author(s):  
T. Green ◽  
A. B. Turner
Keyword(s):  
Pressure Distribution ◽  
Static Pressure ◽  
Three Dimensional ◽  
Computer Code ◽  
Rotor Blades ◽  
Rotor Speed ◽  
Turbine Stage ◽  
Flow Rates ◽  
Static Pressure Distribution ◽  
Axial Clearance

The upstream wheelspace of an axial air turbine stage complete with nozzle guide vanes (NGVs) and rotor blades (430 mm mean diameter) has been tested with the objective of examining the combined effect of NGVs and rotor blades on the level of mainstream ingestion for different seal flow rates. A simple axial clearance seal was used with the rotor spun up to 6650 rpm by drawing air through it from atmospheric pressure with a large centrifugal compressor. The effect of rotational speed was examined for several constant mainstream flow rates by controlling the rotor speed with an air brake. The circumferential variation in hub static pressure was measured at the trailing edge of the NGVs upstream of the seal gap and was found to affect ingestion significantly. The hub static pressure distribution on the rotor blade leading edges was rotor speed dependent and could not be measured in the experiments. The Denton three-dimensional C.F.D. computer code was used to predict the smoothed time-dependent pressure field for the rotor together with the pressure distribution downstream of the NGVs. The level and distribution of mainstream ingestion, and thus the seal effectiveness, was determined from nitrous oxide gas concentration measurements and related to static pressure measurements made throughout the wheelspace. With the axial clearance rim seal close to the rotor the presence of the blades had a complex effect. Rotor blades in connection with NGVs were found to reduce mainstream ingestion seal flow rates significantly, but a small level of ingestion existed even for very high levels of seal flow rate.

403 On Rotor Performance and Blade-to-Blade Static Pressure Distribution in Contra-Rotating Axial Flow Pump

2001 ◽  
Vol 2001 (0) ◽  
pp. 119-120
Author(s):  
Akinori FURUKAWA ◽  
Yinchun CAO ◽  
Kusuo OKUMA ◽  
Takahiro CHONO ◽  
Satoshi WATANABE
Keyword(s):  
Pressure Distribution ◽  
Static Pressure ◽  
Axial Flow ◽  
Static Pressure Distribution ◽  
Axial Flow Pump ◽  
Flow Pump

Performance of a Mixed Flow Pump with Varying Tip Clearance: Part 1

1996 ◽  
Vol 210 (4) ◽  
pp. 305-318 ◽  
Author(s):  
T K Saha ◽  
S Soundranayagam
Keyword(s):  
Angular Momentum ◽  
Flow Field ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Flow Reversal ◽  
Tip Clearance ◽  
Mixed Flow ◽  
Three Dimensional Flow ◽  
Specific Speed ◽  
Flow Pump

Measurements of the three-dimensional flow field entering and leaving a mixed flow pump of non-dimensional specific speed k = 1.89 [ Ns = 100 r/min (metric)] are discussed as a function of flowrate. Flow reversal at inlet at reduced flows is seen to result in abnormally high total pressures in the casing region, but causes no noticeable discontinuities on the head-flow characteristics. Inlet prerotation is associated with the transport of angular momentum by the reversal eddy and begins with the initiation of flow reversal.

Research on the Geometry Parameters of Diffuser Vane Influence on the Performance of Bulb Tubular Pumping System

2017 ◽  
Author(s):  
Yan Jin ◽  
Junxin Wu ◽  
Hongcheng Chen ◽  
Chao Liu
Keyword(s):  
Three Dimensional ◽  
Axial Flow ◽  
Design Parameters ◽  
Hydraulic Loss ◽  
Three Dimensional Flow ◽  
Pump System ◽  
Pumping System ◽  
Axial Flow Pump ◽  
Cfd Method ◽  
Flow Pump

Diffuser vane of tubular pump is different with that of the axial flow pump, since the diffusion angle after the impeller is larger than as usual, which is an important part of bulb tubular pump system. By calculating the hydraulic loss of each part of bulb tubular pump system, it is found that the hydraulic loss of diffuser vane is in large proportion of the whole hydraulic loss. For this situation, focuses on the design parameters of diffuser vane such as diffuser vane length, unilateral edge diffusion angle, equivalent diffusion angle are necessary. In this paper, CFD method is used to simulate the turbulent flow in a bulb tubular pumping system with two different diffuser vanes. The three dimensional flow fields in the whole passage of pumping system with different diffuser vanes are obtained. The results show that all the main geometry parameters of the diffuser vane design affect the performances of tubular pumping system, it should be chosen the parameters reasonably based on the actual situation.

The Use of a Circumferentially Nonuniform Stator to Attenuate Harmful Aerodynamic and Mechanical Interactions in an Advanced Mixed Flow Splittered Rotor/Tandem Variable Stator LP Compressor

2005 ◽  
Author(s):  
M. T. Barton ◽  
D. P. Gentile
Keyword(s):  
Pressure Distribution ◽  
Computer Model ◽  
Static Pressure ◽  
Pressure Variation ◽  
Test Sequence ◽  
Optimized Design ◽  
Angle Distribution ◽  
Gas Generator ◽  
Mixed Flow ◽  
Static Pressure Distribution

A potential flow computer model that can handle blade row interaction problems has been used to analyze the circumferential static pressure distribution at the trailing edge plane of an advanced mixed flow splittered rotor low pressure compressor produced by a downstream tandem stator/strut system. The computer model is based on the Douglas-Neumann formulation and features a powerful automated optimization feature which can define a restagger pattern that will either minimize stator blade-to-blade loading differences or minimize the circumferential static pressure nonuniformity on a preselected axial plane. The latter approach was used presently to design a circumferentially nonuniform stagger angle distribution for the second row of the tandem stator that reduced the circumferential static pressure variation, and consequently its harmonic excitation, on the upstream rotor. Comparison between the predicted static pressure distribution for the baseline case (with uniform stagger angles) and the optimized design showed a dramatic reduction in the circumferential pressure variation. Fourier analyses of the pressure distributions confirmed a substantial decrease in the magnitude of the harmonic index thought to be responsible for the observed severe rotor vibration. The analytical results were confirmed by back-to-back engine tests of the baseline and restaggered tandem stators, where light probe measurements of splitter blade synchronous response showed a proportional decrease in rotor response for the optimized stator configuration. The restagger was implemented quickly and easily using simple modifications to the stator unison ring. With the high splitter blade deflections reduced to an acceptable level, the engine was able to safely accelerate through the former prohibited speed range and continue with the planned test sequence. The restaggered stator design and test effort, from initial problem statement through a successful demonstration test in the gas generator, was accomplished in less than 6 weeks.

Modelling of Incompressible Three-Dimensional Flow in Rotating Turbomachinery Passages

2002 ◽  
Author(s):  
C. Cravero ◽  
A. Satta ◽  
M. Marini
Keyword(s):  
Compressible Flows ◽  
Incompressible Flows ◽  
Three Dimensional ◽  
Inviscid Flow ◽  
Mixed Flow ◽  
Three Dimensional Flow ◽  
Pump Impeller ◽  
Preconditioning Technique ◽  
Cfd Method ◽  
Flow Pump

A CFD method, previously developed by the authors for compressible flows, has been modified through a preconditioning technique to account for purely incompressible flows. Such a code is used to compute three-dimensional flows in a mixed flow pump impeller at design and off-design conditions. The results of the inviscid flow approach are critically discussed by comparison to available experimental data.

scholarly journals Prediction of 3-D Viscous Flow of Centrifugal Impeller With Tip-Clearance: Part 2 — Mixed-Flow Water Pump

1997 ◽  
Author(s):  
E. Y. K. Ng
Keyword(s):  
Static Pressure ◽  
Internal Flow ◽  
Tip Clearance ◽  
Fine Tuning ◽  
Navier Stokes ◽  
Centrifugal Impeller ◽  
Mixed Flow ◽  
Static Pressure Distribution ◽  
Time Marching ◽  
Flow Pump

This paper describes an extension of 3D time-marching compressible Navier-Stokes solver (Part 1) for an incompressible application through the pseudo-compressibility technique suggested by Chorin. Effect of tip clearances on the mixed-flow pump is investigated. Static pressure distribution and intricate internal flow pattern is reasonably well predicted. Fine-tuning of the pseudo-compressibility parameter and grid size is required for improve convergence and stability.

Research on a Full Three-Dimenional Inverse Method for the Mixed-Flow Pump Runner

2002 ◽  
Author(s):  
Honggang Fan ◽  
Naixiang Chen ◽  
Lin Yang ◽  
Zhaohui Xu ◽  
Lunfu Qu ◽  
...  
Keyword(s):  
Inverse Method ◽  
Three Dimensional ◽  
New Method ◽  
Periodic Flow ◽  
Mean Flow ◽  
Mixed Flow ◽  
Three Dimensional Flow ◽  
Dimensional Flow ◽  
Blade Shape ◽  
Flow Pump

In this paper, a full three-dimensional inverse method for the design of mixed-flow pump runner is described. The three-dimensional flow in the runner is decomposed into a tangential mean flow and a tangential periodic flow. The blades are represented by superposition of vortices and sources on the blade mean surface, and the blade mean surface is determined by the inverse method. In this method, the distribution of the circumferentially mean swirl VRθ on the meridional geometry of the runner is prescribed and the corresponding blade shape is computed iteratively. The new method is applied to the design of a mixed-flow pump runner and the result is satisfactory.

A New Three-Dimensional Viscous Inverse Design Method for Axial Compressor Blade

2016 ◽  
Author(s):  
Zhaowei Liu ◽  
Hu Wu
Keyword(s):  
Pressure Distribution ◽  
Static Pressure ◽  
Design Method ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Design Procedure ◽  
Inverse Design ◽  
Blade Surface ◽  
Static Pressure Distribution ◽  
Inverse Design Method

A recently developed aerodynamic inverse design method for axial compressor is presented in this paper. The inverse design method is based on solving the three-dimensional Reynolds-averaged Navier-Stokes equations. Blade surface static pressure distribution is prescribed before the design procedure. A new inverse design boundary condition is established based on the conservation of Riemann invariant on the blade surface. Blade profile is constantly modified by a virtual wall velocity which is obtained from the difference between the current and prescribed static pressure. The dynamic mesh theory is used to update the computation mesh where the shape of the blade is changing during the design process. The design procedure finishes after the prescribed static pressure distribution on the blade surface is satisfied. The method is first validated by a blade recovery test. It is then used to redesign the NASA Rotor 67.

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