2010
17
6
6
0
1

Eect of Different Configurations on 3D Analysis of Flow Through Stay Vanes and Guide Vanes of a Francis Turbine
http://scientiairanica.sharif.edu/article_3365.html
1
Stay and guide vanes (distributor) are essential parts of a turbine. They are used to control
the
ow rate and to appropriately transfer the
ow momentum to the runner. In this work,
ow through
the distributor is analyzed. For various Boundary Conditions (BC) and dierent congurations, threedimensional
ows in the distributor of a Francis turbine are evaluated and compared with each other. The
numerical simulations were carried out using Fluent software and the results were validated with a GAMM
Francis turbine, where the geometry and detailed best eciency measurements were publically available.
In these simulations, the
ow was assumed to be steady and the eect of turbulence was included using
the k ???? " turbulence model. The study showed that an accurate prediction of velocity and pressure elds
through the distributor may be obtained by considering a representative runner chamber with a single
passage, including one blade of a stay and guide vane conguration. Furthermore, the corresponding
needed computational resources for such an analysis are quite modest.
0
Stay and guide vanes (distributor) are essential parts of a turbine. They are used to control
the
ow rate and to appropriately transfer the
ow momentum to the runner. In this work,
ow through
the distributor is analyzed. For various Boundary Conditions (BC) and dierent congurations, threedimensional
ows in the distributor of a Francis turbine are evaluated and compared with each other. The
numerical simulations were carried out using Fluent software and the results were validated with a GAMM
Francis turbine, where the geometry and detailed best eciency measurements were publically available.
In these simulations, the
ow was assumed to be steady and the eect of turbulence was included using
the k ???? " turbulence model. The study showed that an accurate prediction of velocity and pressure elds
through the distributor may be obtained by considering a representative runner chamber with a single
passage, including one blade of a stay and guide vane conguration. Furthermore, the corresponding
needed computational resources for such an analysis are quite modest.
Keywords: Francis turbine; Stay vane; Guide vane; 3D simulation.
0
0


B.
Firoozabadi
Department of Mechanical Engineering,Sharif University of Technology
Iran
email@email.com


R.
Dadfar
Department of Mechanical Engineering,Sharif University of Technology
Iran
acviwpjt@scientiaunknown.non


G.
Ahmadi
Department of Mechanical Engineering,Clarkson University
Iran
ldpqnrji@scientiaunknown.non
Francis turbine
Stay vane
Guide vane
3D simulation
1

TwoDimensional Numerical Investigation of a Micro Combustor
http://scientiairanica.sharif.edu/article_3366.html
1
In this paper, a twodimensional numerical approach is used to study the eect of micro
combustor height, mass
ow rate and external convection heat transfer coecient on the temperature and
species mass fraction proles. A premixed mixture of H2Air with a multistep chemistry is used. The
transient gas phase energy and species conservation equations result in an AdvectionDiusionReaction
system that leads to two sti systems of PDEs. In the present work, the computational domain is
solved through the Strang splitting method, which is suitable for a nonlinear sti system of PDEs. A
revised boundary condition for the velocity equation is applied and its eect on the
ow characteristics is
investigated. The results show that both convection heat transfer coecient and micro combustor height
have a signicant eect on the combustion and heat transfer rates in the micro scales. Also increasing
the convective heat transfer coecient and decreasing the height and inlet mixture velocity, decreases
temperature and active radicals along the micro combustor. In addition, the slip
ow and thermal creep
boundary conditions in the studied scales have no signicant eect on the dierent parameters, but changes
slightly the cross section proles of the temperature. The 2D numerical results show that the micro
combustion must be treated as two dimensional.
0
In this paper, a twodimensional numerical approach is used to study the eect of micro
combustor height, mass
ow rate and external convection heat transfer coecient on the temperature and
species mass fraction proles. A premixed mixture of H2Air with a multistep chemistry is used. The
transient gas phase energy and species conservation equations result in an AdvectionDiusionReaction
system that leads to two sti systems of PDEs. In the present work, the computational domain is
solved through the Strang splitting method, which is suitable for a nonlinear sti system of PDEs. A
revised boundary condition for the velocity equation is applied and its eect on the
ow characteristics is
investigated. The results show that both convection heat transfer coecient and micro combustor height
have a signicant eect on the combustion and heat transfer rates in the micro scales. Also increasing
the convective heat transfer coecient and decreasing the height and inlet mixture velocity, decreases
temperature and active radicals along the micro combustor. In addition, the slip
ow and thermal creep
boundary conditions in the studied scales have no signicant eect on the dierent parameters, but changes
slightly the cross section proles of the temperature. The 2D numerical results show that the micro
combustion must be treated as two dimensional.
Keywords: Micro combustor; Numerical; Combustion; Microscale; Twodimensional.
0
0


M.S.
Saidi
Department of Mechanical Engineering,Sharif University of Technology
Iran
dzwgnvmz@scientiaunknown.non


Abolfazl
Irani Rahaghi
Department of Mechanical Engineering,Sharif University of Technology
Iran
ulunilxx@scientiaunknown.non


M. B.
Shafii
Department of Mechanical Engineering,Sharif University of Technology
Iran
mbbvbkvn@scientiaunknown.non


M. H.
Saidi
Department of Mechanical Engineering,Sharif University of Technology
Iran
plzypquy@scientiaunknown.non
Micro combustor
numerical
Combustion
Microscale
Twodimensional
1

Rayan: A Polyhedral Grid Colocated Incompressible Finite Volume Solver (Part I: Basic Design Features)
http://scientiairanica.sharif.edu/article_3367.html
1
In this work, basic design features of Rayan are documented. One of the new design
features presented in this work is the way Rayan handles polyhedral grids. Grid denition is combined
with the denition of the structure of the sparse coecient matrix, thereby releasing a considerable
part of the memory used by the grid to store otherwise required faces belonging to the cell part of the
connectivity description. The key idea is to use a uniform way for creating the structure of the coecient
matrix from the grid connectivity description and to access that data when computing the elements of
the coecient matrix. This saving requires many modications to the computational algorithm details,
which are addressed. Computational method features include a SIMPLEbased pressurevelocity coupling
and colocated variable arrangement in which all
ow variables are stored at cell centers, and mass
uxes
are stored on face centers. Also handling convective and diusive
uxes is described. The throughput is
benchmark validated and shows second order truncation properties, both in time and space.
0
In this work, basic design features of Rayan are documented. One of the new design
features presented in this work is the way Rayan handles polyhedral grids. Grid denition is combined
with the denition of the structure of the sparse coecient matrix, thereby releasing a considerable
part of the memory used by the grid to store otherwise required faces belonging to the cell part of the
connectivity description. The key idea is to use a uniform way for creating the structure of the coecient
matrix from the grid connectivity description and to access that data when computing the elements of
the coecient matrix. This saving requires many modications to the computational algorithm details,
which are addressed. Computational method features include a SIMPLEbased pressurevelocity coupling
and colocated variable arrangement in which all
ow variables are stored at cell centers, and mass
uxes
are stored on face centers. Also handling convective and diusive
uxes is described. The throughput is
benchmark validated and shows second order truncation properties, both in time and space.
Keywords: Arbitrary polyhedral; Unstructured; Unsteady; Incompressible; Colocated.
0
0


M.S.
Saidi
Department of Mechanical Engineering,Sharif University of Technology
Iran
dzwgnvmz@scientiaunknown.non


M.
SANI
Department of Mechanical Engineering,Sharif University of Technology
Iran
ottvvavv@scientiaunknown.non
Arbitrary polyhedral
Unstructured
Unsteady
Incompressible
Colocated
1

Analysis of Manipulators Using SDRE: A Closed Loop Nonlinear Optimal Control Approach
http://scientiairanica.sharif.edu/article_3368.html
1
In this paper, the State Dependent Riccati Equation (SDRE) method is implemented on
robotic systems such as a mobile twolinks planar robot and a xed 6R manipulator with complicated
dynamic equations. Dynamic modelings of both cases are presented using the Lagrange method.
Afterwards, the Dynamic Load Carrying Capacity (DLCC), which is an important characteristic of robots,
is calculated for these two systems. DLCC is calculated for the predened endeector path, where motor
torque limits and tracking error constraints are imposed for this calculation. For a mobile twolinks planar
robot, the stability constraint is discussed by applying a zero moment point approach. A nonlinear feedback
control law is designed for the fully nonlinear dynamics of two cases using a nonlinear closedloop optimal
control method. For solving the SDRE equation that appears in the optimal control solution, a power
series approximation method is applied. DLCC is obtained, subject to accuracy and torque constraints,
by applying this feedback control law for the square and linear path of the endeector for mobile twolink
and a 6R manipulator, respectively. Finally, simulations are done for both cases and the DLCC of
manipulators is determined. Also, actual endeector positions, required control eorts and the angular
position and velocity of joints are presented for full load conditions, and results are discussed
0
In this paper, the State Dependent Riccati Equation (SDRE) method is implemented on
robotic systems such as a mobile twolinks planar robot and a xed 6R manipulator with complicated
dynamic equations. Dynamic modelings of both cases are presented using the Lagrange method.
Afterwards, the Dynamic Load Carrying Capacity (DLCC), which is an important characteristic of robots,
is calculated for these two systems. DLCC is calculated for the predened endeector path, where motor
torque limits and tracking error constraints are imposed for this calculation. For a mobile twolinks planar
robot, the stability constraint is discussed by applying a zero moment point approach. A nonlinear feedback
control law is designed for the fully nonlinear dynamics of two cases using a nonlinear closedloop optimal
control method. For solving the SDRE equation that appears in the optimal control solution, a power
series approximation method is applied. DLCC is obtained, subject to accuracy and torque constraints,
by applying this feedback control law for the square and linear path of the endeector for mobile twolink
and a 6R manipulator, respectively. Finally, simulations are done for both cases and the DLCC of
manipulators is determined. Also, actual endeector positions, required control eorts and the angular
position and velocity of joints are presented for full load conditions, and results are discussed
Keywords: Mobile manipulator; 6R robot; Nonlinear optimal control; DLCC; SDRE
0
0


M.
Irani
Research Center,Sharif University of Technology
Iran
yzmgiyud@scientiaunknown.non


M. H.
Korayem
Department of Mechanical Engineering,Iran University of Science and Technology
Iran
hkorayem@iust.ac.ir


S.
Rafee Nekoo
Department of Mechanical Engineering,Iran University of Science and Technology
Iran
plochfym@scientiaunknown.non
Mobile manipulator
6R robot
Nonlinear optimal control
DLCC
SDRE
1

Experimental Investigation of Transition on a Plunging Airfoil
http://scientiairanica.sharif.edu/article_3369.html
1
Extensive tests were carried out on a section of a wind turbine blade. The eect of reduced
frequency on the boundary layer transition point of the model oscillating in plunge has been investigated.
The spatialtemporal progressions of the transition point and the state of the unsteady boundary layer were
measured using multiple hotlm sensors. The measurements showed that reduced frequency highly aects
variations of the transition point and results in a hysteresis loop in the dynamic transition locations. The
dominated frequencies of the boundary layer are found to be a function of the reduced frequency and mean
angle of attack.
0
Extensive tests were carried out on a section of a wind turbine blade. The eect of reduced
frequency on the boundary layer transition point of the model oscillating in plunge has been investigated.
The spatialtemporal progressions of the transition point and the state of the unsteady boundary layer were
measured using multiple hotlm sensors. The measurements showed that reduced frequency highly aects
variations of the transition point and results in a hysteresis loop in the dynamic transition locations. The
dominated frequencies of the boundary layer are found to be a function of the reduced frequency and mean
angle of attack.
Keywords: Boundary layer transition; Plunging; Reduced frequency; Airfoil; Wind turbine.
0
0


M. R.
Soltani
Department of Aerospace Engineering,Sharif University of Technology
Iran
jzufniwp@scientiaunknown.non


F.
Rasi Marzabadi
Department of Mechanical Engineering,Sharif University of Technology
Iran
iusiieik@scientiaunknown.non
Boundary layer transition
Plunging
Reduced frequency
Airfoil
Wind Turbine
1

Experimental and Numerical Analysis of Turbulent Air Flow Around a Surface Mounted Hemisphere
http://scientiairanica.sharif.edu/article_3370.html
1
The air
ow field around a surface mounted hemisphere for different velocities is
investigated experimentally and numerically. Hotfilm anemometry is used in a wind tunnel to analyze
the
ow structure for different regions of
ow domain around the hemisphere. The
ow Reynolds number
is varied based on the hemisphere diameter and free stream velocities. The air velocity is taken as 5, 7
and 8.5 m/s, with corresponding Reynolds numbers of 35000, 50000 and 64000. To illustrate the
ow
pattern around the hemisphere, variations of
ow velocity at various vertical sections along the midplane,
and crossstream velocities for various surfaces and heights, are measured and plotted. Corresponding
numerical solutions are also carried out to visualize the
ow reversal, horseshoe vortices and recirculation
zones around and downstream of the hemisphere. It is concluded that the
ow is highly Reynolds number
dependent, especially at the reversed
ow region upstream and downstream of the hemisphere. Moreover,
the eect of hemisphere location in the tunnel is studied, and velocity distributions are compared and
presented in the wake of the hemisphere for constant free stream velocity.
0
The air
ow field around a surface mounted hemisphere for different velocities is
investigated experimentally and numerically. Hotfilm anemometry is used in a wind tunnel to analyze
the
ow structure for different regions of
ow domain around the hemisphere. The
ow Reynolds number
is varied based on the hemisphere diameter and free stream velocities. The air velocity is taken as 5, 7
and 8.5 m/s, with corresponding Reynolds numbers of 35000, 50000 and 64000. To illustrate the
ow
pattern around the hemisphere, variations of
ow velocity at various vertical sections along the midplane,
and crossstream velocities for various surfaces and heights, are measured and plotted. Corresponding
numerical solutions are also carried out to visualize the
ow reversal, horseshoe vortices and recirculation
zones around and downstream of the hemisphere. It is concluded that the
ow is highly Reynolds number
dependent, especially at the reversed
ow region upstream and downstream of the hemisphere. Moreover,
the eect of hemisphere location in the tunnel is studied, and velocity distributions are compared and
presented in the wake of the hemisphere for constant free stream velocity.
Keywords: Hotfilm anemometer; Reversed
ow; Reynolds number; Wake structure; Turbulent
ow.
0
0


M.
Yaghoubi
Department of Mechanical Engineering,Shiraz University
Iran
qkkjeukb@scientiaunknown.non


M.M.
Tavakol
Department of Mechanical Engineering,Shiraz University
Iran
wneawdtd@scientiaunknown.non
Hotfilm anemometer
Reversed ow
Reynolds number
Wake structure
Turbulent ow
1

Experimental Study of Small and Medium Break LOCA in the TTL2 ThermoHydraulic Test Loop and Its Modeling with RELAP5/MOD3.2 Code
http://scientiairanica.sharif.edu/article_3371.html
1
Small and medium break LOCA accidents at low pressure and under low velocity conditions
have been studied in the TTL2 Thermohydraulic Test Loop, experimentally. TTL2 is a thermal
hydraulic test facility which is designed and constructed in NSTRI to study thermal hydraulic parameters
under normal operational and accident conditions of nuclear research reactors. A nodalization has been
developed for the TTL2 and experimental results have been compared with RELAP5/MOD3.2 results.
The considered accidents are a 25% and 50% cold leg break without emergency core cooling systems.
Results show good agreement between experiments and RELAP5/MOD3.2 results. This research provides
experimental data for evaluation of thermo hydraulic codes for nuclear research reactors, and veries
that RELAP5/MOD3.2 has a good capability to estimate the thermal hydraulic behavior of low pressure
and low velocity thermal hydraulic systems, such as research reactors under steady state and transient
conditions.
0
Small and medium break LOCA accidents at low pressure and under low velocity conditions
have been studied in the TTL2 Thermohydraulic Test Loop, experimentally. TTL2 is a thermal
hydraulic test facility which is designed and constructed in NSTRI to study thermal hydraulic parameters
under normal operational and accident conditions of nuclear research reactors. A nodalization has been
developed for the TTL2 and experimental results have been compared with RELAP5/MOD3.2 results.
The considered accidents are a 25% and 50% cold leg break without emergency core cooling systems.
Results show good agreement between experiments and RELAP5/MOD3.2 results. This research provides
experimental data for evaluation of thermo hydraulic codes for nuclear research reactors, and veries
that RELAP5/MOD3.2 has a good capability to estimate the thermal hydraulic behavior of low pressure
and low velocity thermal hydraulic systems, such as research reactors under steady state and transient
conditions.
Keywords: TTL2 thermal hydraulic test loop; LOCA; RELAP5/MOD3.2; Experimental results; Code
validation; Research reactor.
0
0


M.
Taherzadeh
Department of Energy and Environmental Engineering,Sharif University of Technology
Iran
fmsklyhp@scientiaunknown.non


J.
Jafari
Department of Nuclesr Engineering,Sharif University of Technology
Iran
zgenbhdg@scientiaunknown.non


H.
Arabnezhad
Department of Energy and Environmental Engineering,Sharif University of Technology
Iran
yeaqusuf@scientiaunknown.non


N.
Vosoughi
National Nuclear Safety Department,Atomic Energy Organization of Iran
Iran
email@email.com
TTL2 thermal hydraulic test loop
LOCA
RELAP5/MOD3.2
Experimental results
Code validation
Research reactor