CFD analysis of flow through mixed flow compressor under various operating conditions

Save this PDF as:
 WORD  PNG  TXT  JPG

Size: px
Start display at page:

Download "CFD analysis of flow through mixed flow compressor under various operating conditions"

Transcription

1 1 CFD analysis of flow through mixed flow compressor under various operating conditions D. Ramesh Rajakumar 1 M.Govardhan 2 S.Ramamurthy 3 Abstract- Performance of mixed flow compressor with un-shrouded impeller strongly depends upon unsteady, asymmetrical flow fields in the axial directions. The flow through the mixed flow compressor stage is complex due to three-dimensional shape of flow channel. A three-dimensional turbulent flow through a single stage mixed flow compressor is numerically analyzed using commercial software to understand the complex flow behavior inside the impeller channel and near the tip gap. The analysis showed scope for improvement in design of the compressor for better performance in terms of efficiency and operating range. Keywords-Mixed flow compressor, surge, stall, choke, CFD, tip Clearance, compressible flow, periodic, grids and jet-wake. 1 INTRODUCTION 1.1 Motivation Mixed flow Compressor stage is favored for applications in small gas turbine engines as it provides smaller frontal area and high thrust to weight ratio. The efficiency and reliability of the compressor depends to a great extent on flow behavior in its flow passage and flow near shroud (tip) gap. It is well known that the interaction between mixed flow impeller and diffuser substantially influences the flow field and performance of both the components and thus the entire compressor stage. It is therefore, necessary to study and understand the complex flow field inside the flow channel of the mixed flow compressor. 1.2 Background Most of the pioneering works in design and analysis of mixed flow compressor started in 1940s and 50s. Work presented by Austin King et al. in 1942, was probably one of the earliest works regarding mixed flow compressors [1]. They experimentally investigated a parallel cut-off mixed flow impeller with several tip clearances to study the effect of tip clearance. Stanitz [4] described a method for design and analysis of one-dimensional compressible flow in vane-less diffusers of radial and mixed flow compressors including effects of friction, heat transfer and area change. Hah et al. [3] developed a fully elliptical three-dimensional viscous flow analysis method with a finite volume relaxation procedure to compute the flow inside the centrifugal impeller. 1 Scientist, National Trisonic Aerodynamic Facility CSIR-National Aerospace Laboratories, Bangalore-India, Proffessor, Department of Mechanical Engineering, Indian Institute of Technology Madras, Chennai, India, Specialist Consultant, NCAD, CSIR-National Aerospace Laboratories Bangalore- India, Ramamurthy and Murugesan [8] presented a method to design centrifugal compressor geometry using analytical approach to get optimum geometry. Patrik et al. [6] studied the performance of eddy-viscosity, Baldwin-Lomax and Chien k-ε, and low Reynolds number turbulence models and applied to the simulation of a flow in the NASA lowspeed compressor. The k-ε prediction was better than the other models. Pavel Simvnov et al. [7] have adopted numerical simulation of three dimensional flow in a centrifugal compressor stage with a diffuser of variable geometry using the commercial ANSY CFX code. They observed that the total pressure ratio distribution was not favorable in case of larger radial gap. Predictions are very close to the experimental results. Engine [2] described a three dimensional CFD simulation of the flow field in three different un shrouded centrifugal fan with varying tip clearances from 5 mm to 30 mm. He used commercial CFD code; fluent with k-ε two equation turbulence model in order to study the effect of different tip clearances. Krain and Hoffmann [5] have described the development of an improved high pressure ratio centrifugal compressor using analytical approach. A 3-D laser velocity meter was used to probe the flow inside the channel. No specific literature is available on flow simulation of mixed flow compressor. A reliable prediction of the flow field in the mixed flow compressor is regarded as a challenge. 1.3 Applications Mixed flow compressors are used in engines installed in short-range missiles, unmanned aerial vehicles, vehicles used for reconnaissance and in helicopters. These compressors produce moderate stage pressure-ratios of the order of 3.5 to 6 with the available materials like titanium alloys.

2 2 2 OBJECTIVES In this work, computational investigations are carried out to get the stage performance map with tip clearance of 0.5 mm for different operating speeds and mass flow rates covering the complete operating range from choke to surge. The computational simulations are done at five different speeds. Mixed flow impeller was designed for 2.72 kg/s and static to total pressure ratio of 3.8 with design speed of rpm. The complex flow inside the impeller channel is studied at different flow conditions. Specifications of the mixed flow compressor are shown in Table 1. 3 GEOMETRIC MODELING AND MESHING 3.1 Modeling Figure-1 shows the CAD model of compressor stage designed and generated in solid works CAD package. As the domain is axi-symmetric, a single channel consisting of one main blade and one splitter blade is considered for flow analysis. A vane-less space is provided downstream of the impeller is also considered. TABLE 1 Specifications of mixed flow impeller Impeller inlet parameter Value Impeller inlet tip diameter Impeller inlet hub diameter d1it d1ih (m) (m) Impeller rotational speed N (RPM) Hub to tip diameter ratio 1ih 1 it d d 0.40 Relative blade angle at tip Relative blade angle at hub Impeller exit parameter Impeller exit tip diameter Impeller exit hub diameter β 1it (deg) 61.8 β1ih d2it d2ih (m) (deg) (m) b Impeller exit blade height 2i (m) Relative blade angle at tip Relative blade angle at hub β2iti β 2ihI (deg) (deg) α 70 Absolute flow angle 2it (deg) Impeller main blades 11 Impeller splitter blades 11 Fig.1. CAD model of mixed flow impeller Impeller domain is generated using Gambit turbo tool preprocessor. Turbo tool was used for constant tip clearance configuration of 0.5 mm. The flow domain is divided into multiple volumes to form cube like structure so as to fit hexahedral element. Meshing was carried out using Gambit preprocessor. Hexahedral mesh elements were used in all volumes except near the clearance region over the main blade and splitter blade. Grid independence study was done for and elements with zero tip clearance and result is shown in Fig.2. The result shows that number of elements beyond one lakh has no influence on the performance of compressors. However, higher elements are considered for analysis due to zero skewed elements. 3.2 computational methodology For the present work, computations were performed using commercial code namely Fluent. A 3D viscous flow through impeller was analyzed. Segregated solver is used. The numerical fluxes are estimated with first order upwind scheme.

3 3 Fig.2. Grid independence study For the present analysis there are elements are used. The mesh geometry is shown in Fig.3. Table 2, below gives the elements in different regions. TABLE 2 Number of elements at domain magnitude from its initial value and the integrated residuals of all the variables were reduced by six orders of magnitude, the solution was considered as converged. The mass flow summary, the residual history of the variables and the monitor point values were used to judge the convergence behavior of the theoretical analyzed results. The mass imbalance was checked after the solution was converged. In all the cases the observed imbalance in mass flow rate was as low as 0.001%. 3.3 Boundary Conditions Figure 4 shows the flow domain along with boundary conditions assigned in the present analysis. Inlet boundary conditions used were total pressure, total temperature, and absolute flow angle. The distribution of these quantities was assumed constant throughout inlet boundary and hence single value was given. At exit, static pressure (sometimes termed as backpressure) was specified. Periodic boundary conditions were imposed on side faces of tip clearance, upstream and downstream of the impeller blade. The shroud casing was considered stationary. Hub surface and blades of impeller were specified as rotating frame. Fluid volume Surface mesh Solid mesh size Number of cells Shroud clearance Pave Hex/cooper impeller pave Tet/hybrid total Fig.4. Flow domain and BCS Fig.3. Typical mesh of the computational domain The continuity equation, which governs mass conservation, is used to determine the pressure field in the pressurebased method. Turbulence is modeled using standard k-ε model. When the integrated residual of the pressure correction equation was reduced by four orders of 4.0 RESULTS AND DISCUSSIONS 4.1 Performance characteristics The performance of the compressor estimated for various operating speeds with 0.5mm tip clearance from the CFD code is shown in Fig.5. The performance of the impeller was obtained for five speeds, which includes 60%, 75%, 90%, 100% and 105% of the design speed. At each speed the complete impeller operating range (choke to surge) was obtained. The total to total pressure ratio is plotted against mass flow parameter for different operating speeds. It is observed from this figure that at design speed compressor shows choke mass flow rate of 3.29 kg/s whereas the

4 4 surging mass flow rate is around 2.39 kg/s. The impeller design mass flow rate at the design speed is 2.73 kg/sec. Hence compressor at design speed has roughly about 37% surge margin. The estimated pressure ratio (4.50) is slightly lower than design pressure ratio (4.55) due to the inaccuracy in the loss models used in the design. The performance at speed higher than design speed shows a maximum mass flow rate that can be allowed through the impeller is 2% of design mass flow rate. The isentropic efficiency of the impeller was estimated from the impeller total to total pressure ratio and total to total temperature ratio for 0.5mm tip clearance at different speeds. The variation of impeller isentropic efficiency for different speeds that were considered in Fig. 5 is shown in Fig. 6. The peak efficiency of the impeller for various speeds is around 91%, which corresponds to flow having zero incidence at impeller inlet. The impeller design efficiency is 93.8%. On either side of the peak efficiency point the impeller efficiency drops. The sharp drop in efficiency is noticed towards choking side. The lowest efficiency value which corresponds to unstable operating point at different speeds increases with increase in speed. This compressor was tested in closed circuit compressor test rig with vane-less configuration up to rpm. Vane less diffuser outlet static pressure and impeller inlet static pressure were measured for different mass flow conditions The measured stage pressures are plotted against measured mass flow for five different speeds. Through Fluent code, for these speeds and inlet flow conditions the outlet pressure and mass flow through the compressor are estimated. The estimated pressure ratio from CFD is plotted against mass flow rate and compared with experimental values for different speeds. The performance graph obtained is shown in Fig.7. Fig.7.Comparison of performance. Fig.5. Impeller pressure ratio It is observed from this figure that the agreement between CFD and experimental results is good at all speeds. Estimated mass flow is 7.8 % (average) lower than the measured mass flow due to blockage is not considered in the design. This is attributed to small error in mass flow measurement in experimental investigations. 4.2 Blade loading To study the variation of static pressure on the blade suction and pressure surfaces, different operating point at rpm is selected and these points are indicated in figure 9 as A, B, C, D, E and F. These operating points were selected such that they are close to surge, design and choke conditions. These points on the graph are represented as A, C and F. At these selected points the variation of static pressure along the blade surface length is shown in Figs. 10a, 10b and 10c. The local static pressure is normalized with inlet total pressure. The local surface distance is normalized with total surface distance. In each figure, the static pressure variation at three different locations namely, hub, mean and tip section are shown. Fig.6. Impeller efficiency

5 5 Fig.9. Operating points for flow studies Fig.10a.Blad static pressure variation It is observed that a cross over occurs in static pressure distribution curves at choke flow rate, indicating reduction in blade loading. As the mass flow rate is reduced, the pressure distribution curve improves and blade loading increases. Fig.10b. Blade static pressure variation Fig.10c. Blade static pressure variation At the surge point there is drop in blade loading. At each station, the area under pressure distribution curve is higher at the tip section compared to hub section. This behavior is not seen at the surge flow rate. Hence the tip section is highly loaded as the work done is highest at tip section. It is also observed that the static pressure across the blade length increases uniformly from inlet to outlet indicating continuous pressure rise. This behavior is observed at all locations except at choke mass flow. 4.3 Flow angle variations The flow angles at impeller exit was estimated from CFD results at rpm for three operating points A, C and F as indicated in Fig.9. The meridional plane considered is slightly away from the impeller exit. These angles being calculated from the local values of velocities namely U, W and C. The local position of each velocity vector at impeller exit is being captured by local co-ordinates. The relative flow angle and absolute flow angle variation with respect to normalized arc length at three span wise location at impeller exit are shown in Figs. 11a-11d. The spanwise locations being taken one at mid wall (50% of blade height) and one at very close to the shroud wall (95% of blade height). The variation of flow angles at shroud wall represents the tip clearance effects. The relative flow angle variation at impeller exit at 95% of blade height is shown in Fig.11a.The locations of pressure and suction surface of the adjacent blades are indicated as PS and SS in this Figure. It is observed that very close to the blade locations the relative flow angle drops at operating points A and C where as in the blade passage the flow angles are higher than the blade angle. The design blade outlet angle at shroud is 58.5 deg. At operating point A, the flow angle is higher than blade angle by about 8 degrees and at design point the flow angle is slightly higher than the blade angle. The difference in the flow angle and the blade angle represents the slip. It shows the slip increases from operating point C to A. At the operating point it is observed that the flow angle is lower than the

6 6 blade angle by about 8 deg. However it is seen from Fig.11b, the absolute flow angle decreases from surge point to choke point. This is because as the operating points moves from A to F the mass flow rate increases and the pressure ratio drops. The reduction in pressure ratio indicate the drop in work done by the impeller, hence the tangential component of absolute velocity at impeller exit reduces. As the mass flow increases, the meridional component of absolute velocity increases. The combined effect is reduction in absolute flow angle at operating point F. The variation in absolute flow angle is very predominant as the mass flow rate is increased. This will have a large effect on the diffuser producing large negative incidence. The typical change in flow angle at the blade locations will have large influence on the diffuser flow as the number of diffuser blades are fraction of number of impeller blades. The flow angle variation very close to the blades is very large due to the tip leakage flows, which is not observed at 50 % of blade height. Figures 11c-11d represents flow angle variation at impeller exit at 50% of the blade height for same operating points considered in the previous case. Here the relative flow angle variation with respect to operating point shows the flow angle increases with decrease in mass flow rate. But the average value of flow angle is higher than the blade angle at operating points A and C. The design blade angle at 50% of blade height is 52.6 deg. The absolute flow angles remain constant over the blade pitch for a given operating point except close to the blade locations. The variation in the flow angle near the blade locations are smaller than the variation at 95% of the blade height, indicating the influence of tip clearance flow is marginally felt. Fig. 11c. Relative flow angle at 50% blade height for outlet of impeller Fig. 11a.Relative flow angle at 95% blade height for outlet of impeller Fig. 11b. Absolute flow angle at 95% blade height for impeller outlet Fig.11d. Absolute flow angle at 50% blade height for impeller outlet

7 7 4.5 Relative Mach number and velocity variation in flow channel To study the flow behavior inside the impeller channel, different meridional planes namely Inlet, P1, P2, P3, P4, P5, P6 and outlet are considered. Among these planes, four planes namely P1, P4, P6 and impeller outlet planes are used to represent the variations of relative velocities for clarity. The representation of the planes is shown in Figure 12a and the relative Mach number plot for different flow conditions at the different planes is shown in Figure 12b. It is observed from Fig.12b that the relative Mach number at impeller outlet is uniform and increase from surge to choke flow conditions. At inlet plane, the relative Mach Number for each flow condition increases from hub to tip as the blade speed increases and inlet absolute velocity is axial and uniform. Within the blade channel, at plane P4 and P6, the relative velocity is not uniform. Fig.13a.Relative velocity variation at operating point -C In this figure relative velocity is being plotted over two blade pitch so that at any location within the blade channel one main blade and one splitter blade are present. In each figure P and S represents pressure and suction surfaces of the adjacent blades and hub and shroud locations are also marked. Fig. 12a. Meridional planes Fig.13b.Relative velocity variation at operating point A Fig.12b.Relative Mach number contours It is observed for the impeller outlet plane the relative velocity decreases from suction surface to pressure surface at all meridional locations except at shroud region indicating the flow behaves like a potential flow. It is also seen that the relative velocity in the circumferential as well as in the meridional directions remains constant and do not show any variation. However the magnitude of the relative velocity increases from surge to choke operating point. It is also seen that there is no jet-wake pattern indicated in some of the literatures. This shows the geometry of the meridional shape plays an important role in generating such (jet-wake) flow. The variations of relative velocity normalized with respect to tip speed for the impeller outlet plane at different operating points are shown in Figs.13a-13c.

8 8 7 NOMENCLATURES Fig.13c.Relative velocity variation at operating point- F It is inferred that typical flow pattern namely jet-wake as observed in radial flow impellers are absent in the case of mixed flow impellers. 5 CONCLUSIONS There is close match between experimental and CFD results. The estimated pressure ratio (4.50) is slightly lower than design pressure ratio (4.55) due to the inaccuracy in the loss models used in the design. The performance at speed higher than design speed (105%) shows a maximum mass flow rate that can be allowed through the impeller is 2% of design mass flow rate. The compressor at design speed has roughly about 37% surge margin. The surface pressure distribution indicate the blade loading increases from hub to shroud at a given mass flow rate and the blade loading increases as the operating point moves from choke to surge. The local static pressure on the blade surface increases from inlet to outlet showing continuous pressure rise. Flow angle at impeller outlet is uniform from hub to shroud at design point and shows variations at choke and surge flow conditions. Velocity within the channel is uniform and the conventional jet-wake pattern is not observed in mixed flow compressor that is prominent in radial compressor. 6 ACKNOWLEDGEMENTS The authors would like to thank The Director NAL for the his approval for publishing this paper and V. Nagarajan, HOD, NTAF, Mr.M.N. Varadarajan, Janakirama Reddy, Rajesh Yemandi of CLOCTER for their valuable support during the experiments. C absolute velocity (m/s) P pressure (Pa) W relative velocity (m/s) U impeller tip velocity (m/s) Mass flow parameter = m (T 01/ T 01ref) / (P 01/ P 01ref) y/t normalized distance from suction to pressure surface z/b normalized distance from hub to shroud Greek symbols α β absolute flow angle( deg.) relative flow angle(deg.) Subscripts 1 impeller inlet 2 impeller outlet 3 diffuser outlet o total quantity s static quantity 8 REFERENCES [1] Austin King, J. and Edward, G.,1942. Performance Characteristics of Mixed flow impeller and vaned diffuser with several modifications, NACA-WR-E197. [2] Engin T., study of tip clearance effects in centrifugal fns with unshrouded impellers using computational fluid dynamics. Proc.IMech vol.220 parta: J. power and energy, pp [3] Hah, C., Application of viscous flow computations for the aerodynamic performance of a backswept impeller at various operating conditions, J. of turbomachinery, Tran. of ASME, vol. 110, pp [4] John D. Stanitz,, One Dimensional compressible flow in Vanless Diffusers of radial and Mixed-flow centrifugal compressors including Effects of friction heat transfer and area change. NACA TN [5] Krain.H and Hoffmann.B,, Flow study of a Redesigned H- Pressure-Ratio Centrifugal Compressor, J. of propulsion and Power, Vol.24, No.5, pp [6] Patrik, Rautaheimo, P., and Salminen, J., Numerical simulation of the flow in the NASA low-speed centrifugal compressor, International Jl. of turbo and jet engines, Vol. 20, pp [7] Pavel E. Smirnov and Thorsten Hansen., Numerical simulation of turbulent flows in centrifugal compressors stages with different radial gaps, proceedings of GT , ASME Turbo Expo 2007, power for land, sea and air, may 14-17,Montreal, Canada, pp1-10. [8] Ramamurthy, S. and Murugesan, K., An analytic approach to design centrifugal impeller geometry, Proceedings of NCABE 96.

EXPERIMENTAL INVESTIGATIONS ON MIXED FLOW IMPELLER AND VANE DIFFUSER UNDER VARIOUS OPERATING CONDITIONS

EXPERIMENTAL INVESTIGATIONS ON MIXED FLOW IMPELLER AND VANE DIFFUSER UNDER VARIOUS OPERATING CONDITIONS Proceedings of the ASME 2012 International Mechanical Engineering Congress & Exposition, November 9-15, 2012, Houston, Texas, USA IMECE2012 IMECE2012-85695 EXPERIMENTAL INVESTIGATIONS ON MIXED FLOW IMPELLER

More information

Design and Analysis of a High Pressure Ratio Mixed Flow Compressor Stage

Design and Analysis of a High Pressure Ratio Mixed Flow Compressor Stage Design and Analysis of a High Pressure Ratio Mixed Flow Compressor Stage Gaurav Giri 1 and Abdul Nassar. 2 SoftInWay Turbomachinery Solutions Pvt Ltd. 70/10, Cunningham Road, Bangalore, KA, 560052, India

More information

Study of Secondary Flow Modifications at Impeller Exit of a Centrifugal Compressor

Study of Secondary Flow Modifications at Impeller Exit of a Centrifugal Compressor Open Journal of Fluid Dynamics, 2012, 2, 248-256 http://dx.doi.org/10.4236/ojfd.2012.24a029 Published Online December 2012 (http://www.scirp.org/journal/ojfd) ABSTRACT Study of Secondary Flow Modifications

More information

Computational fluid dynamics analysis of a mixed flow pump impeller

Computational fluid dynamics analysis of a mixed flow pump impeller MultiCraft International Journal of Engineering, Science and Technology Vol. 2, No. 6, 2010, pp. 200-206 INTERNATIONAL JOURNAL OF ENGINEERING, SCIENCE AND TECHNOLOGY www.ijest-ng.com 2010 MultiCraft Limited.

More information

OPTIMIZATION OF SINGLE STAGE AXIAL FLOW COMPRESSOR FOR DIFFERENT ROTATIONAL SPEED USING CFD

OPTIMIZATION OF SINGLE STAGE AXIAL FLOW COMPRESSOR FOR DIFFERENT ROTATIONAL SPEED USING CFD http:// OPTIMIZATION OF SINGLE STAGE AXIAL FLOW COMPRESSOR FOR DIFFERENT ROTATIONAL SPEED USING CFD Anand Kumar S malipatil 1, Anantharaja M.H 2 1,2 Department of Thermal Power Engineering, VTU-RO Gulbarga,

More information

EFFECT OF LEADING EDGE SWEEP ON THE PERFORMANCE OF A CENTRIFUGAL COMPRESSOR IMPELLER. Abstract 1. INTRODUCTION

EFFECT OF LEADING EDGE SWEEP ON THE PERFORMANCE OF A CENTRIFUGAL COMPRESSOR IMPELLER. Abstract 1. INTRODUCTION EFFECT OF LEADING EDGE SWEEP ON THE PERFORMANCE OF A CENTRIFUGAL COMPRESSOR Abstract IMPELLER Ch. Sivaji Ganesh 1, *Q. H. Nagpurwala 2, C. S. Bhaskar Dixit 3 1 Student, M. Sc. [Engg.], 2 Professor, 3 Professor

More information

A COMPARATIVE STUDY OF MIX FLOW PUMP IMPELLER CFD ANALYSIS AND EXPERIMENTAL DATA OF SUBMERSIBLE PUMP

A COMPARATIVE STUDY OF MIX FLOW PUMP IMPELLER CFD ANALYSIS AND EXPERIMENTAL DATA OF SUBMERSIBLE PUMP IMPACT: International Journal of Research in Engineering & Technology (IMPACT: IJRET) ISSN 2321-8843 Vol. 1, Issue 3, Aug 2013, 57-64 Impact Journals A COMPARATIVE STUDY OF MIX FLOW PUMP IMPELLER CFD ANALYSIS

More information

CFD Analysis and Experimental Study on Impeller of Centrifugal Pump Alpeshkumar R Patel 1 Neeraj Dubey 2

CFD Analysis and Experimental Study on Impeller of Centrifugal Pump Alpeshkumar R Patel 1 Neeraj Dubey 2 IJSRD - International Journal for Scientific Research & Development Vol. 3, Issue 2, 21 ISSN (online): 2321-613 Alpeshkumar R Patel 1 Neeraj Dubey 2 1 PG Student 2 Associate Professor 1,2 Department of

More information

Higher Gas Turbine Operation Flexibility by Improved Diffuser Vanes of a Radial Compressor

Higher Gas Turbine Operation Flexibility by Improved Diffuser Vanes of a Radial Compressor Higher Gas Turbine Operation Flexibility by Improved Diffuser Vanes of a Radial Compressor STAR EUROPEAN CONFERENCE 2011 23 March 2011 Amsterdam, The Netherlands Dipl.-Ing. Anis Haj Ayed GmbH, Aachen,

More information

The Effect of Impeller Width on the Location of BEP in a Centrifugal Pump

The Effect of Impeller Width on the Location of BEP in a Centrifugal Pump The Effect of Impeller Width on the Location of BEP in a Centrifugal Pump Vinayak Manur 1, Sharanabasappa 2, M. S. Hebbal 3 P.G.Students, Department of Mechanical Engineering, Basaveshwar Engineering College,

More information

Numerical Investigation of Inlet Distortion on an Axial Flow Compressor Rotor with Circumferential Groove Casing Treatment

Numerical Investigation of Inlet Distortion on an Axial Flow Compressor Rotor with Circumferential Groove Casing Treatment Chinese Journal of Aeronautics 21(2008) 496-505 Chinese Journal of Aeronautics www.elsevier.com/locate/cja Numerical Investigation of Inlet Distortion on an Axial Flow Compressor Rotor with Circumferential

More information

Computational Analysis of the S Airfoil Aerodynamic Performance

Computational Analysis of the S Airfoil Aerodynamic Performance Computational Analysis of the 245-3S Airfoil Aerodynamic Performance Luis Velazquez-Araque and Jiří Nožička 2 Department of Mechanical Engineering National University of Táchira, San Cristóbal 5, Venezuela

More information

The Aerodynamic Design and Investigation of Loading Distribution of a Mixed Flow Compressor

The Aerodynamic Design and Investigation of Loading Distribution of a Mixed Flow Compressor Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 00 (2014) 000 000 www.elsevier.com/locate/procedia APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology,

More information

ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT

ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT P.Sethunathan 1, M.Niventhran 2, V.Siva 2, R.Sadhan Kumar 2 1 Asst.Professor, Department of Aeronautical Engineering,

More information

Wind tunnel effects on wingtip vortices

Wind tunnel effects on wingtip vortices 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 2010, Orlando, Florida AIAA 2010-325 Wind tunnel effects on wingtip vortices Xin Huang 1, Hirofumi

More information

Flow Through Axial and Centrifugal Compressors by Kartik Sharma Mentors Prof. Gautam Biswas Prof. Subrata Sarkar

Flow Through Axial and Centrifugal Compressors by Kartik Sharma Mentors Prof. Gautam Biswas Prof. Subrata Sarkar 6 th Indo-German Winter Academy 2007 IIT Guwahati, India, December 13-19, 2007 Flow Through Axial and Centrifugal Compressors by Kartik Sharma Mentors Prof. Gautam Biswas Prof. Subrata Sarkar Outline of

More information

Impeller Treatment for a Centrifugal Fan using Splitter Vanes A CFD Approach

Impeller Treatment for a Centrifugal Fan using Splitter Vanes A CFD Approach , July 6-8, 2011, London, U.K. Impeller Treatment for a Centrifugal Fan using Splitter Vanes A CFD Approach Madhwesh N. 1, K. Vasudeva Karanth 2 and N. Yagnesh Sharma 3, Member, IAENG Abstract In a centrifugal

More information

Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of Supersonic Convergent Divergent Nozzle

Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of Supersonic Convergent Divergent Nozzle RESEARCH ARTICLE OPEN ACCESS Investigation on Divergent Exit Curvature Effect on Nozzle Pressure Ratio of Supersonic Convergent Divergent Nozzle Shyamshankar.M.B*, Sankar.V** *(Department of Aeronautical

More information

ZIN Technologies PHi Engineering Support. PHi-RPT CFD Analysis of Large Bubble Mixing. June 26, 2006

ZIN Technologies PHi Engineering Support. PHi-RPT CFD Analysis of Large Bubble Mixing. June 26, 2006 ZIN Technologies PHi Engineering Support PHi-RPT-0002 CFD Analysis of Large Bubble Mixing Proprietary ZIN Technologies, Inc. For nearly five decades, ZIN Technologies has provided integrated products and

More information

A Research on the Airflow Efficiency Analysis according to the Variation of the Geometry Tolerance of the Sirocco Fan Cut-off for Air Purifier

A Research on the Airflow Efficiency Analysis according to the Variation of the Geometry Tolerance of the Sirocco Fan Cut-off for Air Purifier A Research on the Airflow Efficiency Analysis according to the Variation of the Geometry Tolerance of the Sirocco Fan Cut-off for Air Purifier Jeon-gi Lee*, Choul-jun Choi*, Nam-su Kwak*, Su-sang Park*

More information

Design and Numerical Flow Analysis of Expansion Deflection Nozzle

Design and Numerical Flow Analysis of Expansion Deflection Nozzle Design and Numerical Flow Analysis of Expansion Deflection Nozzle Shaik Abdul Muwaaz 1, Nazumuddin Shaik 2 Post Graduate Student, Assistant Professor 1 Shaik Abdul Muwaaz, Aerospace Department, Nimra Institute

More information

Analysis of pressure losses in the diffuser of a control valve

Analysis of pressure losses in the diffuser of a control valve Analysis of pressure losses in the diffuser of a control valve Petr Turecký 1, Lukáš Mrózek 2*, Ladislav Taj 2, and Michal Kolovratník 3 1 ENVIROS, s.r.o., Dykova 53/10, 101 00 Praha 10-Vinohrady, Czech

More information

High Swept-back Delta Wing Flow

High Swept-back Delta Wing Flow Advanced Materials Research Submitted: 2014-06-25 ISSN: 1662-8985, Vol. 1016, pp 377-382 Accepted: 2014-06-25 doi:10.4028/www.scientific.net/amr.1016.377 Online: 2014-08-28 2014 Trans Tech Publications,

More information

Numerical Analysis of Wings for UAV based on High-Lift Airfoils

Numerical Analysis of Wings for UAV based on High-Lift Airfoils Numerical Analysis of Wings for UAV based on High-Lift Airfoils Sachin Srivastava Department of Aeronautical Engineering Malla Reddy College of Engineering & Technology, Hyderabad, Telangana, India Swetha

More information

FLOW CONSIDERATIONS IN INDUSTRIAL SILENCER DESIGN

FLOW CONSIDERATIONS IN INDUSTRIAL SILENCER DESIGN FLOW CONSIDERATIONS IN INDUSTRIAL SILENCER DESIGN George Feng, Kinetics Noise Control, Inc., 3570 Nashua Drive, Mississauga, Ontario Vadim Akishin, Kinetics Noise Control, Inc., 3570 Nashua Drive, Mississauga,

More information

EXPERIMENTAL STUDY OF WIND PRESSURES ON IRREGULAR- PLAN SHAPE BUILDINGS

EXPERIMENTAL STUDY OF WIND PRESSURES ON IRREGULAR- PLAN SHAPE BUILDINGS BBAA VI International Colloquium on: Bluff Bodies Aerodynamics & Applications Milano, Italy, July, 2-24 8 EXPERIMENTAL STUDY OF WIND PRESSURES ON IRREGULAR- PLAN SHAPE BUILDINGS J. A. Amin and A. K. Ahuja

More information

International Journal of Technical Research and Applications e-issn: , Volume 4, Issue 3 (May-June, 2016), PP.

International Journal of Technical Research and Applications e-issn: ,  Volume 4, Issue 3 (May-June, 2016), PP. DESIGN AND ANALYSIS OF FEED CHECK VALVE AS CONTROL VALVE USING CFD SOFTWARE R.Nikhil M.Tech Student Industrial & Production Engineering National Institute of Engineering Mysuru, Karnataka, India -570008

More information

AIRFOIL PROFILE OPTIMIZATION OF AN AIR SUCTION EQUIPMENT WITH AN AIR DUCT

AIRFOIL PROFILE OPTIMIZATION OF AN AIR SUCTION EQUIPMENT WITH AN AIR DUCT THERMAL SCIENCE, Year 2015, Vol. 19, No. 4, pp. 1217-1222 1217 AIRFOIL PROFILE OPTIMIZATION OF AN AIR SUCTION EQUIPMENT WITH AN AIR DUCT by Li QIU a,b, Rui WANG a,*, Xiao-Dong CHEN b, and De-Peng WANG

More information

New Technologies applied to the design and optimization of tunnel ventilation systems

New Technologies applied to the design and optimization of tunnel ventilation systems New Technologies applied to the design and optimization of tunnel ventilation systems Ing. Justo Suárez Area Manager - ZITRON Dot. Ing. Massimiliano Bringiotti Managing Director - GEOTUNNEL Ing. Ana Belén

More information

NUMERICAL AND EXPERIMENTAL INVESTIGATION OF THE FLOWFIELD IN A BLOWDOWN WIND TUNNEL

NUMERICAL AND EXPERIMENTAL INVESTIGATION OF THE FLOWFIELD IN A BLOWDOWN WIND TUNNEL ICAS 2002 CONGRESS NUERICAL AND EXPERIENTAL INVESTIGATION OF THE FLOWFIELD IN A BLOWDOWN WIND TUNNEL Ali Rebaine, ahmood Khalid, Cabot Broughton and Fred Ellis Institute for Aerospace Research, National

More information

Centre for Offshore Renewable Energy Engineering, School of Energy, Environment and Agrifood, Cranfield University, Cranfield, MK43 0AL, UK 2

Centre for Offshore Renewable Energy Engineering, School of Energy, Environment and Agrifood, Cranfield University, Cranfield, MK43 0AL, UK 2 Fluid Structure Interaction Modelling of A Novel 10MW Vertical-Axis Wind Turbine Rotor Based on Computational Fluid Dynamics and Finite Element Analysis Lin Wang 1*, Athanasios Kolios 1, Pierre-Luc Delafin

More information

Application of Computational Fluid Dynamics to Compressor Efficiency Improvement

Application of Computational Fluid Dynamics to Compressor Efficiency Improvement Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 1994 Application of Computational Fluid Dynamics to Compressor Efficiency Improvement J.

More information

Turbine Blade Tip Leakage Flow Control by Unsteady Periodic Wakes of Upstream Blade Row

Turbine Blade Tip Leakage Flow Control by Unsteady Periodic Wakes of Upstream Blade Row Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 80 (2014 ) 202 215 3 rd International Symposium on Aircraft Airworthiness, ISAA 2013 Turbine Blade Tip Leakage Flow Control

More information

CFD ANALYSIS OF CENTRIFUGAL PUMP IMPELLER HAVING DIFFERENT EXIT BLADE WIDTH, EXIT DIAMETER AND TRAILING EDGE BLADE ANGLE TO ENHANCE PERFORMANCE

CFD ANALYSIS OF CENTRIFUGAL PUMP IMPELLER HAVING DIFFERENT EXIT BLADE WIDTH, EXIT DIAMETER AND TRAILING EDGE BLADE ANGLE TO ENHANCE PERFORMANCE CFD ANALYSIS OF CENTRIFUGAL PUMP IMPELLER HAVING DIFFERENT EXIT BLADE WIDTH, EXIT DIAMETER AND TRAILING EDGE BLADE ANGLE TO ENHANCE PERFORMANCE AmitKumar 1, Prof. Kamal Kumar Jain 2, Dr.R.KDave3, Asst.

More information

Numerical Computations of Wind Turbine Wakes Using Full Rotor Modeling

Numerical Computations of Wind Turbine Wakes Using Full Rotor Modeling 2012 2nd International Conference on Power and Energy Systems (ICPES 2012) IPCSIT vol. 56 (2012) (2012) IACSIT Press, Singapore DOI: 10.7763/IPCSIT.2012.V56.21 Numerical Computations of Wind Turbine Wakes

More information

OPTIMIZING THE LENGTH OF AIR SUPPLY DUCT IN CROSS CONNECTIONS OF GOTTHARD BASE TUNNEL. Rehan Yousaf 1, Oliver Scherer 1

OPTIMIZING THE LENGTH OF AIR SUPPLY DUCT IN CROSS CONNECTIONS OF GOTTHARD BASE TUNNEL. Rehan Yousaf 1, Oliver Scherer 1 OPTIMIZING THE LENGTH OF AIR SUPPLY DUCT IN CROSS CONNECTIONS OF GOTTHARD BASE TUNNEL Rehan Yousaf 1, Oliver Scherer 1 1 Pöyry Infra Ltd, Zürich, Switzerland ABSTRACT Gotthard Base Tunnel with its 57 km

More information

Numerical Study of Giromill-Type Wind Turbines with Symmetrical and Non-symmetrical Airfoils

Numerical Study of Giromill-Type Wind Turbines with Symmetrical and Non-symmetrical Airfoils European International Journal of Science and Technology Vol. 2 No. 8 October 2013 Numerical Study of Giromill-Type Wind Turbines with Symmetrical and Non-symmetrical Airfoils Prathamesh Deshpande and

More information

ASME International Mechanical Engineering Congress & Exhibition IMECE 2013 November 15-21, 2013, San Diego, California, USA

ASME International Mechanical Engineering Congress & Exhibition IMECE 2013 November 15-21, 2013, San Diego, California, USA ASME International Mechanical Engineering Congress & Exhibition IMECE 2013 November 15-21, 2013, San Diego, California, USA IMECE2013-62734 AERODYNAMIC CHARACTERISTICS OF HORIZONTAL AXIS WIND TURBINE WITH

More information

CFD Simulation of the Flow Through Reciprocating Compressor Self-Acting Valves

CFD Simulation of the Flow Through Reciprocating Compressor Self-Acting Valves Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 1994 CFD Simulation of the Flow Through Reciprocating Compressor Self-Acting Valves P. Cyklis

More information

NUMERICAL INVESTIGATION OF FLOW OVER MULTI- ELEMENT AIRFOILS WITH LIFT-ENHANCING TABS

NUMERICAL INVESTIGATION OF FLOW OVER MULTI- ELEMENT AIRFOILS WITH LIFT-ENHANCING TABS 28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES NUMERICAL INVESTIGATION OF FLOW OVER MULTI- ELEMENT AIRFOILS WITH LIFT-ENHANCING TABS Zhenhui Zhang, Dong Li National Key Laboratory of Science

More information

Performance Analysis of Centrifugal Compressor under Multiple Working Conditions Based on Time-weighted Average

Performance Analysis of Centrifugal Compressor under Multiple Working Conditions Based on Time-weighted Average Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 2014 Performance Analysis of Centrifugal Compressor under Multiple Working Conditions Based

More information

Axial Compressor Design with Counter-Rotation and Variable RPM for Stall Mitigation

Axial Compressor Design with Counter-Rotation and Variable RPM for Stall Mitigation Dissertations and Theses 7-11-2014 Axial Compressor Design with Counter-Rotation and Variable RPM for Stall Mitigation Madhur Tiwari Embry-Riddle Aeronautical University - Daytona Beach Follow this and

More information

Air Craft Winglet Design and Performance: Cant Angle Effect

Air Craft Winglet Design and Performance: Cant Angle Effect Journal of Robotics and Mechanical Engineering Research Air Craft Winglet Design and Performance: Cant Angle Effect Eslam Said Abdelghany 1, Essam E Khalil 2*, Osama E Abdellatif 3 and Gamal elhariry 4

More information

PREDICTION OF TOTAL PRESSURE CHARACTERISTICS IN THE SETTLING CHAMBER OF A SUPERSONIC BLOWDOWN WIND TUNNEL

PREDICTION OF TOTAL PRESSURE CHARACTERISTICS IN THE SETTLING CHAMBER OF A SUPERSONIC BLOWDOWN WIND TUNNEL PREDICTION OF TOTAL PRESSURE CHARACTERISTICS IN THE SETTLING CHAMBER OF A SUPERSONIC BLOWDOWN WIND TUNNEL S R Bhoi and G K Suryanarayana National Trisonic Aerodynamic Facilities, National Aerospace Laboratories,

More information

Steady Analysis of NACA Flush Inlet at High Subsonic and Supersonic Speeds

Steady Analysis of NACA Flush Inlet at High Subsonic and Supersonic Speeds , July 1-3, 2015, London, U.K. Steady Analysis of NACA Flush Inlet at High Subsonic and Supersonic Speeds Taimur A. Shams 1, Masud J 2 Abstract Essence of this research is to report computational analysis

More information

Effect of Upstream Velocity Gradient on the Formation of Sink Vortices in a Jet Engine Test Cell

Effect of Upstream Velocity Gradient on the Formation of Sink Vortices in a Jet Engine Test Cell Effect of Upstream Velocity Gradient on the Formation of Sink Vortices in a Jet Engine Test Cell W. H. Ho, H. Dumbleton, and M.C. Jermy Abstract Vortices can be produced and ingested into the intake of

More information

Numerical Simulation of Flow and Determination of Aerodynamic Forces in the Balanced Control Valve

Numerical Simulation of Flow and Determination of Aerodynamic Forces in the Balanced Control Valve EPJ Web of Conferences 45, 01062 (2013) DOI: 10.1051/ epjconf/ 20134501062 C Owned by the authors, published by EDP Sciences, 2013 Numerical Simulation of Flow and Determination of Aerodynamic Forces in

More information

Aerodynamic investigation of Winglets on Wind Turbine Blades using CFD

Aerodynamic investigation of Winglets on Wind Turbine Blades using CFD Risø-R-1543(EN) Aerodynamic investigation of Winglets on Wind Turbine Blades using CFD Jeppe Johansen and Niels N. Sørensen Risø National Laboratory Roskilde Denmark February 26 Author: Jeppe Johansen

More information

Research and optimization of intake restrictor for Formula SAE car engine

Research and optimization of intake restrictor for Formula SAE car engine International Journal of Scientific and Research Publications, Volume 4, Issue 4, April 2014 1 Research and optimization of intake restrictor for Formula SAE car engine Pranav Anil Shinde Mechanical Engineering,

More information

CFD Analysis on Two Bladed Savonius Wind Turbine With and Without Splitter

CFD Analysis on Two Bladed Savonius Wind Turbine With and Without Splitter CFD Analysis on Two Bladed Savonius Wind Turbine With and Without Splitter Deviprasad N Mirashi 1, Dr. S. Kumarappa 2 1PG student, Dept. of Mechanical Engineering, BIET Davangere, Karnataka, India 2Professor

More information

EFFECT OF GEOMETRIC DISTORTION ON THE FLOW FIELD AND PERFORMANCE OF AN AXISYMMETRIC SUPERSONIC INTAKE

EFFECT OF GEOMETRIC DISTORTION ON THE FLOW FIELD AND PERFORMANCE OF AN AXISYMMETRIC SUPERSONIC INTAKE Indian J.Sci.Res.() : 909-99, 0 ISSN:50-08(Online) ISSN : 0976-876 (Print) EFFECT OF GEOMETRIC DISTORTION ON THE FLOW FIELD AND PERFORMANCE OF AN AXISYMMETRIC SUPERSONIC INTAKE MOHAMMAD FARAHANI a, ALIREZA

More information

Analysis of Wind Turbine Blade

Analysis of Wind Turbine Blade International Journal of Current Engineering and Technology E-ISSN 2277 4106, P-ISSN 2347-5161 2014 INPRESSCO, All Rights Reserved Available at http://inpressco.com/category/ijcet Research Article Analysis

More information

DESIGN OF AN AERODYNAMIC MEASUREMENT SYSTEM FOR UNMANNED AERIAL VEHICLE AIRFOILS

DESIGN OF AN AERODYNAMIC MEASUREMENT SYSTEM FOR UNMANNED AERIAL VEHICLE AIRFOILS DESIGN OF AN AERODYNAMIC MEASUREMENT SYSTEM FOR UNMANNED AERIAL VEHICLE AIRFOILS L. Velázquez-Araque 1 and J. Nožička 1 1 Department of Fluid Dynamics and Power Engineering, Faculty of Mechanical Engineering

More information

Optimization of Ejector's Performance With a CFD Analysis. Amanda Mattos Karolline Ropelato Ricardo Medronho

Optimization of Ejector's Performance With a CFD Analysis. Amanda Mattos Karolline Ropelato Ricardo Medronho Optimization of Ejector's Performance With a CFD Analysis Amanda Mattos Karolline Ropelato Ricardo Medronho 2 Introduction Ejectors Equipment industrially used and based on the Venturi phenomena; With

More information

EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT

EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT Chapter-6 EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT 6.1 Introduction The gurney flap (wicker bill) was a small flat tab projecting from the trailing edge of a wing. Typically it

More information

Analysis of Lift and Drag Forces at Different Azimuth Angle of Innovative Vertical Axis Wind Turbine

Analysis of Lift and Drag Forces at Different Azimuth Angle of Innovative Vertical Axis Wind Turbine International Journal of Energy and Power Engineering 2015; 4(5-1): 12-16 Published online August 31, 2015 (http://www.sciencepublishinggroup.com/j/ijepe) doi: 10.11648/j.ijepe.s.2015040501.12 ISSN: 2326-957X

More information

Study on the Shock Formation over Transonic Aerofoil

Study on the Shock Formation over Transonic Aerofoil Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 2 (2013), pp. 113-118 Research India Publications http://www.ripublication.com/aasa.htm Study on the Shock Formation over

More information

ENGINEERING AUSTRALIA PTY. LTD.

ENGINEERING AUSTRALIA PTY. LTD. POWERTECH ENGINEERING AUSTRALIA PTY. LTD. 15 Lorikeet Street, Terrigal NSW 2260 AUSTRALIA. ACN 102 392 558 Phone: (61) 02 4384 6000. Fax: (61) 02 4384 6200. ABN 63 102 392 558 Email: powerteche@bigpond.com

More information

Investigations on the Aerodynamic Forces of 2-D Square Lattice Tower Section Using CFD

Investigations on the Aerodynamic Forces of 2-D Square Lattice Tower Section Using CFD J. Energy Power Sources Vol. 1, No. 5, 2014, pp. 270-277 Received: August 14, 2014, Published: November 30, 2014 Journal of Energy and Power Sources www.ethanpublishing.com Investigations on the Aerodynamic

More information

Aerodynamically Efficient Wind Turbine Blade S Arunvinthan 1, Niladri Shekhar Das 2, E Giriprasad 3 (Avionics, AISST- Amity University, India)

Aerodynamically Efficient Wind Turbine Blade S Arunvinthan 1, Niladri Shekhar Das 2, E Giriprasad 3 (Avionics, AISST- Amity University, India) International Journal of Engineering Science Invention ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 Volume 3 Issue 4ǁ April 2014ǁ PP.49-54 Aerodynamically Efficient Wind Turbine Blade S Arunvinthan

More information

EXPERIMENTAL INVESTIGATION OF LIFT & DRAG PERFORMANCE OF NACA0012 WIND TURBINE AEROFOIL

EXPERIMENTAL INVESTIGATION OF LIFT & DRAG PERFORMANCE OF NACA0012 WIND TURBINE AEROFOIL EXPERIMENTAL INVESTIGATION OF LIFT & DRAG PERFORMANCE OF NACA0012 WIND TURBINE AEROFOIL Mr. Sandesh K. Rasal 1, Mr. Rohan R. Katwate 2 1 PG Student, 2 Assistant Professor, DYPSOEA Ambi Talegaon, Heat Power

More information

EFFECT OF CORNER CUTOFFS ON FLOW CHARACTERISTICS AROUND A SQUARE CYLINDER

EFFECT OF CORNER CUTOFFS ON FLOW CHARACTERISTICS AROUND A SQUARE CYLINDER EFFECT OF CORNER CUTOFFS ON FLOW CHARACTERISTICS AROUND A SQUARE CYLINDER Yoichi Yamagishi 1, Shigeo Kimura 1, Makoto Oki 2 and Chisa Hatayama 3 ABSTRACT It is known that for a square cylinder subjected

More information

CFD SIMULATIONS OF GAS DISPERSION IN VENTILATED ROOMS

CFD SIMULATIONS OF GAS DISPERSION IN VENTILATED ROOMS CFD SIMULATIONS OF GAS DISPERSION IN VENTILATED ROOMS T. Gélain, C. Prévost Institut de Radioprotection et de Sûreté Nucléaire (IRSN), Saclay, France Abstract In order to better understand the risks due

More information

Development of Gasdynamic Probe for Total Temperature Measurement in gases

Development of Gasdynamic Probe for Total Temperature Measurement in gases ASET 20- National Conference on Emerging Trends in Propulsion Technology Development of Gasdynamic Probe for Total Temperature Measurement in gases K Sathiyamoorthy, Souren Misra 2, Srinivas J, Baskaran

More information

The Effect of Von Karman Vortex Street on Building Ventilation

The Effect of Von Karman Vortex Street on Building Ventilation The Effect of Von Karman Vortex Street on Building Ventilation P.Praveen Kumar Abstract This paper deals with the utilisation of the von Karman vortex street principle to maximise air flow into buildings.

More information

AERODYNAMIC CHARACTER OF PARTIAL SQUEALER TIP ARRANGEMENTS IN AN AXIAL FLOW TURBINE

AERODYNAMIC CHARACTER OF PARTIAL SQUEALER TIP ARRANGEMENTS IN AN AXIAL FLOW TURBINE IGTI/ASME TURBO EXPO 22 June 22 Amsterdam The Netherlands AERODYNAMIC CHARACTER OF PARTIAL SQUEALER TIP ARRANGEMENTS IN AN AXIAL FLOW TURBINE Part : 3 Detailed Aerodynamic Field Visualizations via Three

More information

WIND-INDUCED LOADS OVER DOUBLE CANTILEVER BRIDGES UNDER CONSTRUCTION

WIND-INDUCED LOADS OVER DOUBLE CANTILEVER BRIDGES UNDER CONSTRUCTION WIND-INDUCED LOADS OVER DOUBLE CANTILEVER BRIDGES UNDER CONSTRUCTION S. Pindado, J. Meseguer, J. M. Perales, A. Sanz-Andres and A. Martinez Key words: Wind loads, bridge construction, yawing moment. Abstract.

More information

Determination of the wind pressure distribution on the facade of the triangularly shaped high-rise building structure

Determination of the wind pressure distribution on the facade of the triangularly shaped high-rise building structure Determination of the wind pressure distribution on the facade of the triangularly shaped high-rise building structure Norbert Jendzelovsky 1,*, Roland Antal 1 and Lenka Konecna 1 1 STU in Bratislava, Faculty

More information

Injector Dynamics Assumptions and their Impact on Predicting Cavitation and Performance

Injector Dynamics Assumptions and their Impact on Predicting Cavitation and Performance Injector Dynamics Assumptions and their Impact on Predicting Cavitation and Performance Frank Husmeier, Cummins Fuel Systems Presented by Laz Foley, ANSYS Outline Overview Computational Domain and Boundary

More information

THE EFFECT OF HUB LEAKAGE FLOW ON TWO HIGH SPEED AXIAL FLOW COMPRESSOR ROTORS

THE EFFECT OF HUB LEAKAGE FLOW ON TWO HIGH SPEED AXIAL FLOW COMPRESSOR ROTORS THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS 345 E. 47th St., New York, N.Y. 10017 97-GT-346 The Society shall not be responsible for statements or opinions advanced in papers or diacussion at meetings

More information

Performance of GOE-387 Airfoil Using CFD

Performance of GOE-387 Airfoil Using CFD International Journal of Aerospace Sciences 2017, 5(1): 1-7 DOI: 10.5923/j.aerospace.20170501.01 Performance of GOE-387 Airfoil Using CFD Mohamed A. Fouad Kandil *, Abdelrady Okasha Elnady Mechatronics

More information

A COMPARATIVE FLOW ANALYSIS OF NACA 6409 AND NACA 4412 AEROFOIL

A COMPARATIVE FLOW ANALYSIS OF NACA 6409 AND NACA 4412 AEROFOIL A COMPARATIVE FLOW ANALYSIS OF NACA 6409 AND NACA 4412 AEROFOIL MD. Safayet Hossain 1, Muhammad Ferdous Raiyan 2, Mohammed Nasir Uddin Akanda 3, Nahed Hassan Jony 4 1 Department of Mechanical Engineering,

More information

Effect of attack angle on flow characteristic of centrifugal fan

Effect of attack angle on flow characteristic of centrifugal fan IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Effect of attack angle on flow characteristic of centrifugal fan To cite this article: Y Wu et al 206 IOP Conf. Ser.: Mater. Sci.

More information

Numerical simulation and analysis of aerodynamic drag on a subsonic train in evacuated tube transportation

Numerical simulation and analysis of aerodynamic drag on a subsonic train in evacuated tube transportation Journal of Modern Transportation Volume 20, Number 1, March 2012, Page 44-48 Journal homepage: jmt.swjtu.edu.cn DOI: 10.1007/BF03325776 1 Numerical simulation and analysis of aerodynamic drag on a subsonic

More information

CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT

CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT Magnus effect, simulation, air flow Patryk SOKOŁOWSKI *, Jacek CZARNIGOWSKI **, Paweł MAGRYTA *** CFD SIMULATION STUDY OF AIR FLOW AROUND THE AIRFOIL USING THE MAGNUS EFFECT Abstract The article presents

More information

Blade Design and Performance Analysis of Wind Turbine

Blade Design and Performance Analysis of Wind Turbine International Journal of ChemTech Research CODEN( USA): IJCRGG ISSN : 0974-4290 Vol.5, No.2, pp 1054-1061, April-June 2013 ICGSEE-2013[14 th 16 th March 2013] International Conference on Global Scenario

More information

Review of Variable Geometry Techniques Applied to Enhance the Performance of Centrifugal Compressors

Review of Variable Geometry Techniques Applied to Enhance the Performance of Centrifugal Compressors Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 2000 Review of Variable Geometry Techniques Applied to Enhance the Performance of Centrifugal

More information

JOURNAL PUBLICATIONS

JOURNAL PUBLICATIONS 1 JOURNAL PUBLICATIONS 71. Lee, T., Mageed, A., Siddiqui, B. and Ko, L.S., (2016) Impact of ground proximity on aerodynamic properties of an unsteady NACA 0012 airfoil, submitted to Journal of Aerospace

More information

Static Extended Trailing Edge for Lift Enhancement: Experimental and Computational Studies

Static Extended Trailing Edge for Lift Enhancement: Experimental and Computational Studies Static Extended Trailing Edge for Lift Enhancement: Experimental and Computational Studies T. Liu, J. Montefort, W. Liou Western Michigan University Kalamazoo, MI 49008 and Q. Shams NASA Langley Research

More information

LEADING-EDGE VORTEX FLAPS FOR SUPERSONIC TRANSPORT CONFIGURATION -EFFECTS OF FLAP CONFIGURATIONS AND ROUNDED LEADING-EDGES-

LEADING-EDGE VORTEX FLAPS FOR SUPERSONIC TRANSPORT CONFIGURATION -EFFECTS OF FLAP CONFIGURATIONS AND ROUNDED LEADING-EDGES- ICAS 2002 CONGRESS LEADING-EDGE VORTEX FLAPS FOR SUPERSONIC TRANSPORT CONFIGURATION -EFFECTS OF FLAP CONFIGURATIONS AND ROUNDED LEADING-EDGES- Kenichi RINOIE*, Dong Youn KWAK**, Katsuhiro MIYATA* and Masayoshi

More information

A Numerical Study of Thickness Effect of the Symmetric NACA 4-Digit Airfoils on Self Starting Capability of a 1kW H-Type Vertical Axis Wind Turbine

A Numerical Study of Thickness Effect of the Symmetric NACA 4-Digit Airfoils on Self Starting Capability of a 1kW H-Type Vertical Axis Wind Turbine International Journal of Mechanical Engineering and Applications 2015; 3(3-1): 7-16 Published online February 13, 2015 (http://www.sciencepublishinggroup.com/j/ijmea) doi: 10.11648/j.ijmea.s.2015030301.12

More information

WAKE MODELING OF AN OFFSHORE WINDFARM USING OPENFOAM

WAKE MODELING OF AN OFFSHORE WINDFARM USING OPENFOAM WAKE MODELING OF AN OFFSHORE WINDFARM USING OPENFOAM Alireza Javaheri, Beatriz Canadillas UL International GmbH (DEWI), Ebertstr. 96, 26382 Wilhelmshaven, Germany Summery The premier task of this work

More information

AIAA Brush Seal Performance Evaluation. P. F. Crudgington Cross Manufacturing Co. Ltd. Devizes, ENGLAND

AIAA Brush Seal Performance Evaluation. P. F. Crudgington Cross Manufacturing Co. Ltd. Devizes, ENGLAND AIAA 98-3172 Brush Seal Performance Evaluation P. F. Crudgington Cross Manufacturing Co. Ltd. Devizes, ENGLAND BRUSH SEAL PERFORMANCE EVALUATION AIAA-98-3172 P. F. Crudgington Cross Manufacturing Co. Ltd

More information

School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire MK43 0AL, UK;

School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire MK43 0AL, UK; Energies 2015, 8, 8516-8536; doi:10.3390/en8088516 Article OPEN ACCESS energies ISSN 1996-1073 www.mdpi.com/journal/energies An Iterative Method to Derive the Equivalent Centrifugal Compressor Performance

More information

A new methodology to evaluate the flying shape of a sail

A new methodology to evaluate the flying shape of a sail International conference on Graphics Engineering June 19 th 21 st, 2013 Madrid,Spain INGEGRAF ADM AIP PRIMECA A new methodology to evaluate the flying shape of a sail T. Ingrassia (a), V. Nigrelli (a),

More information

Abstract. 1 Introduction

Abstract. 1 Introduction Developments in modelling ship rudder-propeller interaction A.F. Molland & S.R. Turnock Department of Ship Science, University of Southampton, Highfield, Southampton, S017 IBJ, Hampshire, UK Abstract A

More information

Transitional Steps Zone in Steeply Sloping Stepped Spillways

Transitional Steps Zone in Steeply Sloping Stepped Spillways Transitional Steps Zone in Steeply Sloping Stepped Spillways Jalal Attari 1 and Mohammad Sarfaraz 2 1- Assistant Professor, Power and Water University of Technology, Iran 2- Graduate Student, Department

More information

Experimental Determination of Temperature and Pressure Profile of Oil Film of Elliptical Journal Bearing

Experimental Determination of Temperature and Pressure Profile of Oil Film of Elliptical Journal Bearing International Journal of Advanced Mechanical Engineering. ISSN 2250-3234 Volume 4, Number 5 (2014), pp. 469-474 Research India Publications http://www.ripublication.com Experimental Determination of Temperature

More information

AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF THE AERODYNAMIC CHARACTERISTICS AN OSCILLATORY PITCHING NACA0012 AEROFOIL

AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF THE AERODYNAMIC CHARACTERISTICS AN OSCILLATORY PITCHING NACA0012 AEROFOIL AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF THE AERODYNAMIC CHARACTERISTICS AN OSCILLATORY PITCHING NACA0012 AEROFOIL Ashim Yadav, Simon Prince & Jenny Holt School of Aerospace, Transport and Manufacturing,

More information

AIR FLOW DISTORTION OVER MERCHANT SHIPS.

AIR FLOW DISTORTION OVER MERCHANT SHIPS. AIR FLOW DISTORTION OVER MERCHANT SHIPS. M. J. Yelland, B. I. Moat and P. K. Taylor April 2001 Extended Abstract Anemometers on voluntary observing ships (VOS) are usually sited above the bridge in a region

More information

Numerical Investigation of Suction and Length of Suction Jet on Aerodynamic Characteristics of the NACA 0012 Airfoil

Numerical Investigation of Suction and Length of Suction Jet on Aerodynamic Characteristics of the NACA 0012 Airfoil Numerical Investigation of Suction and Length of Suction Jet on Aerodynamic Characteristics of the NACA 0012 Airfoil Kianoosh Yousefi, S. Reza Saleh, and Peyman Zahedi Abstract In this study, the effect

More information

STUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS

STUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS ICAS 2000 CONGRESS STUDIES ON THE OPTIMUM PERFORMANCE OF TAPERED VORTEX FLAPS Kenichi RINOIE Department of Aeronautics and Astronautics, University of Tokyo, Tokyo, 113-8656, JAPAN Keywords: vortex flap,

More information

Adjustment of the k-ω SST turbulence model for prediction of airfoil characteristics near stall

Adjustment of the k-ω SST turbulence model for prediction of airfoil characteristics near stall Journal of Physics: Conference Series PAPER OPEN ACCESS Adjustment of the -ω SST turbulence model for prediction of airfoil characteristics near stall To cite this article: A A Matyusheno and A V Garbaru

More information

Modeling of Hydraulic Hose Paths

Modeling of Hydraulic Hose Paths Mechanical Engineering Conference Presentations, Papers, and Proceedings Mechanical Engineering 9-2002 Modeling of Hydraulic Hose Paths Kurt A. Chipperfield Iowa State University Judy M. Vance Iowa State

More information

Simulation of Free Surface Flows with Surface Tension with ANSYS CFX

Simulation of Free Surface Flows with Surface Tension with ANSYS CFX Simulation of Free Surface Flows with Surface Tension with ANSYS CFX C. Kurt Svihla, Hong Xu ANSYS, Inc. Abstract Three different test cases involving free surface flows with surface tension were investigated

More information

A Study on the Effects of Wind on the Drift Loss of a Cooling Tower

A Study on the Effects of Wind on the Drift Loss of a Cooling Tower A Study on the Effects of Wind on the Drift Loss of a Cooling Tower Wanchai Asvapoositkul 1* 1 Department of Mechanical Engineering, Faculty of Engineering, King Mongkut s University of Technology Thonburi

More information

Tidal streams and tidal stream energy device design

Tidal streams and tidal stream energy device design Tidal streams and tidal stream energy device design This technical article introduces fundamental characteristics of tidal streams and links these to the power production of tidal stream energy devices.

More information

NUMERICAL SIMULATION OF CROSS-FLOW AROUND FOUR CIRCULAR CYLINDERS IN-LINE SQUARE CONFIGURATION NEAR A PLANE WALL

NUMERICAL SIMULATION OF CROSS-FLOW AROUND FOUR CIRCULAR CYLINDERS IN-LINE SQUARE CONFIGURATION NEAR A PLANE WALL NUMERICAL SIMULATION OF CROSS-FLOW AROUND FOUR CIRCULAR CYLINDERS IN-LINE SQUARE CONFIGURATION NEAR A PLANE WALL A. Grummy Wailanduw 1, Triyogi Yuwono 2 and Wawan Aries Widodo 2 1 Student of Doctoral Program

More information

High Speed Rail Tunnel Aerodynamics: Transient pressure and loadings on fixed tunnel equipment

High Speed Rail Tunnel Aerodynamics: Transient pressure and loadings on fixed tunnel equipment High Speed Rail Tunnel Aerodynamics: Transient pressure and loadings on fixed tunnel equipment Mohammad Tabarra & Richard Sturt Arup, UK Summary: Trains entering tunnels at high speeds can generate highly

More information

Micro Channel Recuperator for a Reverse Brayton Cycle Cryocooler

Micro Channel Recuperator for a Reverse Brayton Cycle Cryocooler Micro Channel Recuperator for a Reverse Brayton Cycle Cryocooler C. Becnel, J. Lagrone, and K. Kelly Mezzo Technologies Baton Rouge, LA USA 70806 ABSTRACT The Missile Defense Agency has supported a research

More information