scholarly journals Computational study on the aerodynamics of a long-shrouded contra-rotating rotor in hover

2019 ◽  
Vol 11 ◽  
pp. 175682931983368
Author(s):  
Chao Huo ◽  
Peng Lv ◽  
Anbang Sun
Keyword(s):  
Flow Field ◽  
Opposite Direction ◽  
Computational Study ◽  
Flow Characteristics ◽  
The Other ◽  
Complex Flow ◽  
Sliding Mesh ◽  
Global Performance ◽  
Mesh Method ◽  
Downstream Flow

This paper aims to investigate the aerodynamics including the global performance and flow characteristics of a long-shrouded contra-rotating rotor by developing a full 3D RANS computation. Through validations by current experiments on the same shrouded contra-rotating rotor, the computation using sliding mesh method and the computational zone with an extended nozzle downstream flow field effectively works; the time-averaged solution of the unsteady computation reveals that more uniform flow presents after the downstream rotor, which implies that the rear rotor rotating at opposite direction greatly compensates and reduces the wake; the unsteady computations further explore the flow field throughout the whole system, along the span and around blade tips. Complex flow patterns including the vortices and their interactions are indicated around the blade roots and tips. For further identifying rotor configurations, the rotor–rotor distance and switching two rotor speeds were studied. The computation reveals that setting the second rotor backwards decreases the wake scale but increases its intensity in the downstream nozzle zone. However, for the effect of switching speeds, computations cannot precisely solve the flow when the rear rotor under the windmill because of the upstream rotor rotating much faster than the other one. All the phenomena from computations well implement the experimental observations.

Analysis of the Full Flow Field of Torque Converter

2012 ◽  
Vol 468-471 ◽  
pp. 674-677 ◽  
Author(s):  
Yu Long Lei ◽  
Chang Wang ◽  
Zheng Jie Liu ◽  
Xing Zhong Li
Keyword(s):  
Flow Field ◽  
Boundary Conditions ◽  
Flow Rate ◽  
Flow Model ◽  
Three Dimensional ◽  
Calculated Data ◽  
Torque Converter ◽  
Three Dimensional Flow ◽  
Sliding Mesh ◽  
Mesh Method

Establish the full three-dimensional flow model of the torque converter, proper mesh the model, select the appropriate boundary conditions, and use the sliding mesh method to deal with the interactions of the impeller, turbine, and reactor in different rotation speeds. Analysis the flow rate, pressure, and the loss of full flow field passage of the torque converter, elaborate the formation mechanism of the flow field, agreement with the experimental date compare to the calculated data, more accurate than the traditional single passage model compare to the full passage model, provide the direction of design optimization of the torque converter.

A Computational Study on the Effect of Angles of Attack on a Double-Cone Type Supersonic Inlet With Bleeding System

2010 ◽  
Author(s):  
Kyung Jin Ryu ◽  
Seol Lim ◽  
Sang Dug Kim ◽  
Dong Joo Song
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Computational Study ◽  
Angle Of Attack ◽  
Flow Characteristics ◽  
Uniform Flow ◽  
Double Cone ◽  
Interface Plane ◽  
Supersonic Inlet ◽  
Cone Type

The flow characteristics on a supersonic inlet with bleeding system at various angles of attack are studied by using computational 3D turbulent flow analysis. A turbulent CSCM compressible upwind flux difference splitting Navier-Stokes method with k-w turbulence model is used to compute the inlet flowfields. MPICH-2.0 library and PC-cluster system are used to reduce computational times. Distortion and average of total pressure recovery at the AIP (aerodynamic interface plane) are used as evaluation criteria of inlet performance. The flow characteristics at zero of angle of attack of double-cone type supersonic inlet without and with bleeding system have been compared. Without bleeding system inlet with the strong SBLI (shock/boundary-layer interaction) induces slow flow recovery near the throat and produces very thick boundary layer downstream. But the bleeding system successfully removes the low energy flow from the boundary layer near the throat. As the angle of attack at the AIP because large, we can see more non-uniform flow field, and the non-uniform flow field is the major aggravating factor of inlet performance.

Investigation on Flow Characteristics and Performance of a Vertical Axis Wind Turbine With Deflector Plates

2019 ◽  
Author(s):  
K. Karthik Selva Kumar ◽  
Vinayak Kulkarni ◽  
Niranjan Sahoo
Keyword(s):  
Wind Turbine ◽  
Computational Study ◽  
Flow Characteristics ◽  
Vertical Axis ◽  
Vertical Axis Wind Turbine ◽  
Near Wake ◽  
Flow Phenomenon ◽  
Sliding Mesh ◽  
And Performance ◽  
Accelerated Flow

Abstract In this article, a 3D computational study has been performed to understand the flow phenomenon over the vertical axis wind turbine with a three-bladed NACA0021. The rotary motion of the VAWT simulated with sliding mesh techniques with reference to the SST-Kω turbulence model using the CFD software. The observed results were found to be having a significant improvement in the enhancement of the power output. Also, the investigation was move forwarded to understand the flow characteristics of the VAWT with the presence of deflector plates in different orientation at the upstream conditions. The present of deflector plates creates an augmented flow phenomenon which creates an accelerated flow at the near wake region, causing a significant improvement in the coefficient of power of the wind turbine.

Experimental Investigation on Aerodynamic Unsteadiness in a Full Scale Gas Turbine Midframe Sector

2013 ◽  
Author(s):  
Matthew J. Golsen ◽  
Jahed Hossain ◽  
Anthony Bravato ◽  
John Harrington ◽  
Joshua Bernstein ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Flow Behavior ◽  
Flow Characteristics ◽  
Mean Flow ◽  
Complex Flow ◽  
Inlet Conditions ◽  
Complicated Geometry ◽  
Downstream Flow ◽  
Complicated Geometries ◽  
Flow Experiments

Aerodynamic unsteadiness generated upstream of the combustor basket via the complicated geometry of a modern gas turbine can lead to incomplete combustion, reduced efficiency, greater pressure drop, flashback, and reduced part life. The MidFrame section encompasses the main gas path from the compressor exit to the turbine inlet. Diffuser performance, support struts, transition pieces, and other flow obstructing geometries can lead to flow unsteadiness which can reduce performance. This study uses a combination of thermal anemometry, pressure microphone, and wall mounted accelerometer measurements to determine the primary unsteadiness frequencies and target their source. Diffuser performance is shown to have a significant impact on the downstream flow behavior. Inlet conditions are modified to provide a separated bottom wall and a fully attached compressor exit diffuser (CED) condition at an area average inlet Mach number of 0.26. Unsteadiness levels are seen to increase as a result of the separated inlet condition while the mean flow characteristics are slightly altered due to the varying exit trajectory of the main core from the CED, nevertheless the overall level of unsteadiness/turbulence is low for such a complex flow field (8 to 11 %). Results of this study can help diagnose and prevent the aforementioned issues for complicated geometries where simple flow experiments fall short.

Computational Analysis of Fluid Flow in Pebble Bed Modular Reactor Using Different Turbulence Models

2010 ◽  
Author(s):  
Akshay Gandhir ◽  
Yassin Hassan
Keyword(s):  
Fluid Flow ◽  
Pressure Drop ◽  
Flow Structure ◽  
Computational Study ◽  
Vortex Formation ◽  
Flow Characteristics ◽  
Turbulence Models ◽  
Packed Bed ◽  
Complex Flow ◽  
Fluid Flow Characteristics

A steady state computational study was done to obtain the pressure drop estimation in different packed bed geometries, and describe the fluid flow characteristics for such complex structures. Two out of the three Bravais lattices were analyzed, namely, simple cubic (symmetric) and body centered cubic (staggered). STARCCM+ commercial CFD software from CD-ADAPCO was used to simulate the flow. To account for turbulence effects standard k-epsilon and realizable k-epsilon models were used. Various cases were analyzed with Modified Reynolds number ranging from 10,000 to 50,000. Each model showed different results as far as the velocity and flow structure is concerned. However, for each case the flow structure showed similar features such as vortex formation downstream and between pebbles due to complex flow separation [1]. The pressure drop obtained from each model was found to be in reasonable agreement with the existing data.

Study of Swirling Air Flow Characteristics in a Lean Direct Injection Combustor

2010 ◽  
Author(s):  
Dipanjay Dewanji ◽  
Arvind G. Rao ◽  
Mathieu Pourquie ◽  
Jos P. van Buijtenen
Keyword(s):  
Numerical Model ◽  
Flow Field ◽  
Swirling Flow ◽  
Direct Injection ◽  
Flow Characteristics ◽  
Single Element ◽  
Complex Flow ◽  
Flow Passage ◽  
Lean Direct Injection ◽  
Entire Flow

This paper investigates the non-reacting aerodynamic flow characteristics in Lean Direct Injection (LDI) combustors. The RANS modeling is used to simulate the turbulent, non-reacting, and confined flow field associated with a single-element and a nine-element LDI combustor. The results obtained from the simulation are compared with some experimental data available in literature. The numerical model, which is in accordance with an experimental combustor, consists of an air swirler with 6 helical axial vanes of 60 degree vane angle and a converging-diverging duct, extending in a square flame tube. The numerical model covers the entire flow passage, including the highly swirling flow passage through the swirler vanes, and the combustion chamber. Simulation has been performed with a low Reynolds number realizable k-ε model and a Reynolds stress turbulence model. It is observed that the computational model is able to predict the central re-circulation zones (CTRZ), the corner recirculation zones, and the complex flow field associated with the adjacent swirlers with reasonable accuracy. The computed velocity components for the single-element case show that the flow field is similar to the experimental observations.

scholarly journals Numerical Study of the Unsteady Flow Characteristics of a Jet Centrifugal Pump under Multiple Conditions

Processes ◽  
2019 ◽  
Vol 7 (11) ◽  
pp. 786
Author(s):  
Rong Guo ◽  
Rennian Li ◽  
Renhui Zhang ◽  
Wei Han
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Centrifugal Pump ◽  
Temporal Evolution ◽  
Guide Vane ◽  
Flow Characteristics ◽  
The Other ◽  
Flow Passage ◽  
Evolution Laws ◽  
Multiple Conditions

To study the reasons for the low efficiency of jet centrifugal pumps (JCPs) and the mechanism of unsteady flow characteristics under multiple conditions, taking a JET750G1 JCP as the object, three-dimensional steady and unsteady numerical calculations of the model pump were carried out using the k–ω turbulence model. The transient fluctuation characteristics of the flow field in the major flow passage components and the spatial and temporal evolution laws of vortices in the rotor–stator cascades were analyzed. The accuracy of the numerical method was verified by experiments. The results show that there are various scales of flow distortion phenomena in the chamber of the JCP, such as eddies, blockage of the flow passage, recirculation, secondary flow, and circulation, which not only cause great hydraulic loss, but also destroy the flow stability, symmetry, and balance in the other flow passage components. This is an important reason for the obviously lower efficiency of a JCP compared to a general centrifugal pump. The spatial and temporal evolution laws of vortices in the rotor–stator cascades are mainly related to the relative positions of the impeller blades and guide vane blades. The formation mechanism of the unsteady flow field fluctuation characteristics of JCPs is mainly related to the number of blades in the rotor–stator cascades and the operation parameters of the pump. The fluctuation intensity of the flow field inside the impeller and guide vane is obviously greater than that in the other flow areas, reflecting that the rotor–stator interaction is the decisive factor affecting the unsteady flow characteristics of a JCP under multiple conditions.

scholarly journals Flow control in supersonic flow field based on micro jets

2019 ◽  
Vol 11 (1) ◽  
pp. 168781401882152 ◽  
Author(s):  
Yanming Liu ◽  
Hong Zhang ◽  
Pingchao Liu
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flow Field ◽  
Flow Characteristics ◽  
Complex Flow ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Vortex Pairs ◽  
Boundary Layer Interaction ◽  
Wave Boundary

The flow field around supersonic aircraft is usually accompanied by complex flow phenomena, such as shock wave and shock wave/boundary layer interaction, which cause some adverse effects on aircraft performance. Seeking effective flow control methods has been a hot topic for many researchers. As an important method to improve the flow characteristics in supersonic flows, micro jet technology and its control mechanism have been paid much attention. In this article, we used compression corner calculation model and conducted detailed numerical investigations in the supersonic flow field with different injection pressure ratios, various actuation positions, and different nozzle types. The interaction between the micro jets and supersonic upstream flows generates complex flow structures, which contain bow shocks, barrel shocks, Mach disk, counter-rotating vortex pairs, and so on. The flow characteristics with micro jet schemes are superior to those in the no-control case. The controlling performance of micro jet is mainly determined by the following aspects. First, the downwash effect of counter-rotating vortex pairs can bring high-energy fluid into the bottom of the boundary layer to activate low-energy fluid and then strengthen the ability of resisting the flow separations. Second, the bow shock, which is generated upstream of the micro jet, significantly decelerates the downstream flows. Thus, the shock intensity at the corner is weakened and the characteristic of shock wave/boundary layer interaction is improved. In addition, the effective function range of MJ, that is, the distance between the counter-rotating vortex pair and the wall surface, is also an important factor. When both the counter-rotating vortex pairs and the bow shock are further from the wall, the flow characteristics around the corner in a larger area can be improved. Research shows that the micro jet scheme with Laval nozzle gives better controlling effect on shock wave/boundary layer interaction when the injection pressure radio is set to be 0.6, with the actuation location being 20 times the jet outlet diameter upstream of the corner.

Detailed Study of Pulsating Flow Performance in a Mixed Flow Turbocharger Turbine

2005 ◽  
Author(s):  
Aaron Costall ◽  
Ricardo F. Martinez-Botas ◽  
Dean Palfreyman
Keyword(s):  
Flow Field ◽  
Combustion Engine ◽  
Flow Direction ◽  
Flow Characteristics ◽  
Pulsating Flow ◽  
Turbine Stage ◽  
Complex Flow ◽  
Pulse Period ◽  
Pulse Profile ◽  
Direction Control

Automotive turbocharger turbines experience a highly unsteady and pulsating flow field due to the abrupt operation of the exhaust valves in a reciprocating internal combustion engine. Previous work has demonstrated and validated against experiment a computational model of a turbine stage under such conditions. The same model is used in the present paper to examine in greater detail the complex flow characteristics observed. The pulsating inlet condition results in a highly disturbed flow field in the turbine stage, the main features of which have already been identified. The effect of the passing of the blades at the volute tongue is observed, and the fluctuating velocity field in the blade passages is seen to lead to poor flow direction control at the turbine inlet and exit. The turbine geometry, calculated for steady flow, is forced to operate away from design conditions for most of the pulse period. Through a detailed analysis of the intricate flow field features at varying instants during the pulse period, this paper highlights areas of the blade geometry and periods in the pulse profile that should be investigated further, such that the integrated performance across the entire pulse cycle can be improved.

scholarly journals Numerical Investigation of Thermal-Flow Characteristics in Heat Exchanger with Various Tube Shapes

2021 ◽  
Vol 11 (20) ◽  
pp. 9477
Author(s):  
Fares Djeffal ◽  
Lyes Bordja ◽  
Redha Rebhi ◽  
Mustafa Inc ◽  
Hijaz Ahmad ◽  
...  
Keyword(s):  
Circular Tube ◽  
Flow Characteristics ◽  
Performance Criterion ◽  
Finned Tube ◽  
The Other ◽  
Thermal Flow ◽  
Axis Ratio ◽  
Thermal Exchange ◽  
Global Performance ◽  
Oval Tube

In this study, eight configurations of oval and flat tubes in annular finned-tube thermal devices are examined and compared with the conventional circular tube. The objective is to assess the effect of tube flatness and axis ratio of the oval tube on thermal-flow characteristics of a three-row staggered bank for Re (2600 ≤ Re ≤ 10,200). It has been observed that the thermal exchange rate and Colburn factor increase according to the axis ratio and the flatness, where O1 and F1 provide the highest values. O1 produces the lowest friction factor values of all the oval tubes at all Re, and F4 gives 13.2–18.5% less friction than the other tube forms. In terms of performance evaluation criterion, all of the tested tubes outperformed the conventional circular tube (O5), with O1 and F1 obtaining the highest values. The global performance criterion of O1 has been found to be 9.6–45.9% higher as compared to the other oval tube geometries at lower values of Re, and the global performance criterion increases with the increase in flatness. The F1 tube shape outperforms all the examined tube designs; thus, this tube geometry suggests that it be used in energy systems.

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