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The Modeling of a Propeller Turbine Runner in 3D Solid Using 3D Equation Curve
in Autodesk Inventor 2015
Article in Applied Mechanics and Materials · June 2016
DOI: 10.4028/www.scientific.net/AMM.842.147
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1
The Modeling of a Propeller Turbine Runner in
3D Solid using 3D Equation Curve in Autodesk
Inventor 2015
Indra Djodikusumo, I Nengah Diasta, and Fachri Koeshardono
Abstract — Published paper on modelling of propeller turbine
blade and runner is not commonly found, especially those using
Autodesk Inventor. One of them is titled CAD Modelling of Axial
Turbine Blade using Autodesk Inventor. However, the road
taken is quite complicated and should be repeated from the
beginning whenever new geometrical characteristics of a new
axial propeller turbine will be modelled. Currently, Autodesk
Inventor has introduced the new tool that help sketching the
spline lines either in 2D plane or 3D space simplifying the task of
3D modelling of propeller turbine blade, called Equation Curve.
The Equation Curve tool requires the codes for creating the
spline lines. To create the codes, two sources have been used:
NACA report no. 460 and modelling methodology proposed by
Milos in his paper. In NACA report no. 460, it is explained that
NACA 4 Digit Series is created by combining mean line with the
thickness variation curve of Gottingen 398 and Clark Y. This
airfoil has 4 different lines with their own equation. The
equations can be used for sketching in 2D plane. However, the
solid model of the runner blade is formed from the airfoils in
cylindrical surface. Then, as explained by Milos in his paper, the
procedure is as follows: sketch the airfoil in 2D plane that is the
tangent of cylindrical surface, move the airfoil to its center, rotate
to its stagger angle, and project it to cylindrical surface. The
result of this process will be the equations of lines in 3D space.
Transform them to the Inventor codes. Input these codes to 3D
Equation Curve tool to create the 4 lines for each cylindrical
surface section of blade. Making the solid model of runner the
following step is required: use loft command to create blade
surfaces, use the stitch command to solidify, use the pattern
command to create other blades, create hub, and lastly combine
blades and hub. The solid model of the runner then is tested by
simulating it using ANSYS Fluent. The hydraulic efficiency of the
model is 85 %.
Index Terms— Propeller Turbine Runner, Propeller Turbine
Blade, Equation Curve, 3D Modeling
This paper was submitted at September 14th 2015.
Indra Djodikusumo is with the Faculty of Mechanical and Aerospace
Engineering, Institute of Technology Bandung, Jalan Ganesha no. 10 Bandung
40132, Indonesia (e-mail: djodikusumo.indra@gmail.com).
I Nengah Diasta is with the Faculty of Mechanical and Aerospace
Engineering, Institute of Technology Bandung, Jalan Ganesha no. 10 Bandung
40132, Indonesia (e-mail: inengahdiasta@gmail.com).
Fachri Koeshardono is with the Faculty of Mechanical and Aerospace
Engineering, Institute of Technology Bandung, Jalan Ganesha no. 10 Bandung
40132, Indonesia (e-mail: fachri_256@students.itb.ac.id).
I.
INTRODUCTION
Published paper on modeling of propeller turbine blade
and runner is not commonly found, especially those using
Autodesk Inventor. One of them is titled CAD Modeling of
Axial Turbine Blade using Autodesk Inventor [1]. The steps of
the modeling strategy in that paper consist of: importing the
3D coordinates of blade profile (airfoils) that can be imported
from Excel by command import points or from other CAD
softwares, creating blade surface, performing extension of the
blade surface, intersecting the blade surface with radial planes
and creating the solid model of the blade [1]. However, the
road taken is quite complicated and should be repeated from
the beginning whenever a new geometrical characteristics of a
new axial propeller turbine will be modelled.
dsec
m/l
L/l
t/l
β∞c
l
z
with
dsec
m/l
L/l
t/l
β∞c
l
z
TABLE I
GEOMETRICAL CHARACTERISTICS OF THE RUNNER BLADE
Sections
0
1
2
3
4
0.400
0.356
0.312
0.268
0.224
4
4
4
4
4
40
40
40
40
40
3
4
5
6
7
20
22
25
29
35
196
176
155
133
111
7
Diameter
NACA maximum camber
NACA maximum camber location
NACA maximum thickness
profile distortion angle
chord length
number of blade
5
0.180
4
40
8
47
89
[m]
[%]
[%]
[%]
[o]
[mm]
[-]
In this paper another approach in modeling of the propeller
turbine blade and runner will be described, where the
technique used is more straightforward. This technique used is
made possible with the new tool introduced in Autodesk
Inventor 2013, called equation curve. The modelling begins
with the geometrical characteristics (Table 1).
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II. SKETCHING STRATEGY
Starting with the geometrical characteristics the blade
profile on the surface of the cylinder will be sketched. In order
to do that the method introduced by Milos has been adopted
[2]. The steps of sketching the blade are as follow: airfoil
design in the own system of representation, the transposition
of the airfoils to the stagger angle into developed plane, and
the transposition of the airfoils from plane on the computing
cylindrical surfaces.
A. Airfoil design in the own system of representation
In accordance with Table 1, the type of airfoil used in this
paper is a NACA 4 Digit Series. This series was introduced to
improve the previous airfoil profiles that could not
systematically provide the correlation between the
aerodynamics characteristics and the variations of shape. As
mentioned in report no. 460, airfoil profiles may be considered
as made up of certain profile thickness forms disposed about
certain mean lines. The major shape variables then become
two, the thickness form and the mean-line form. The thickness
form is of particular importance from a structural standpoint.
On the other hand, the form of the mean line determines
almost independently some of the most important
aerodynamic properties of the airfoil section, e.g., the angle of
zero lift and the pitching-moment characteristics [3].
NACA 4 Digit Series is developed with better efficiency
from the previous two airfoils, Göttingen 398 and Clark Y.
These two airfoils are nearly alike when their camber is
removed (the mean line is straightened). When they are
reduced to the same thickness, the curve would be like the Fig
1 [3].
2
from 0.1015 into 0.1036 [4]. The equation has been modified
and expressed as a thickness variation per chord length (yt/l).
2
!
! $ $
# 0.2969 x - 0.1260 x - 0.3516 # x & +&
l
l
yt t / l #
"l% &
(3)
=
#
&
3
4
l 0,2 #
!x$
!x$
&
# 0.2843 # l & - 0.1036 # l &
&
" %
" %
"
%
As mentioned before the airfoil profiles may be considered
as made up of certain profile thickness forms disposed about
certain mean lines, then the role of the mean line becomes
very important. In the NACA report no. 460 it is stated the
mean lines of certain airfoils in common use were reduced to
the same maximum ordinate and compared it was found that
their shapes were quite different. It was observed, however,
that the range of shapes can be well covered by assuming
some simple shape and varying the maximum ordinate and its
position along the chord. The mean line was, therefore,
arbitrarily defined by two parabolic equations [3].
Some boundary conditions are given to both parabolic
equations. The result is a mean line equations consisting of
two equations in two ranges, namely before and after the
maximum ordinate. Both equations are modified into the
equations of mean line per chord length (yc/l).
0≤ x< L/l
2⎞
⎛
yc
m/ l ⎜ L x ⎛x⎞ ⎟
=
2
⎜
⎟
l (0≤x<L/l ) (L / l)2 ⎜⎝ l l ⎝ l ⎠ ⎟⎠
(4)
L / l ≤ x ≤1
2⎞
⎛
yc
m / l ⎜⎛
L⎞
L x ⎛x⎞ ⎟
=
-⎜ ⎟
⎜1- 2 ⎟ + 2
l ( L/l≤x≤1) (1- L / l)2 ⎜⎝⎝
l⎠
l l ⎝ l ⎠ ⎟⎠
(5)
As described in the report NACA 460, the method of
combining the thickness forms with the mean-line forms is
best described by means of the Fig.2. Referring to the figure,
the ordinate yt of the thickness form is measured along the
Fig. 1 Thickness variation of NACA 4 Digit Series
perpendicular to the mean line from a point on the mean line
If the chord taken along the x axis from 0 to 1 and y is the at the station along the chord corresponding to the value of x
thickness of the profile, the thickness variation could be for which yt is computed. Then points to the formation of the
upper surface and a lower surface of the airfoil can be marked
approximated using the following equation [3].
as (xu, yu) and (xl, yl). In addition to these points, the symbol ϑ
is employed to designate the angle between the tangent to the
2
3
4
± y = 0.2969 x - 0.1260 x - 0.3516 x + 0.2843 x - 0.1015 x (1) mean line and the x axis. In conclusion there would be 4 lines
In order to change the thickness variation to fit a maximum in the airfoil profile: 2 upper lines (Line 1 and Line 2) and 2
thickness value (t), the equation needs to be converted into:
lower lines (Line 3 and Line 4).
yt =
t
0, 2
(0.2969
2
3
x - 0.1260 x - 0.3516 x + 0.2843 x - 0.1015 x
4
)
(2)
The equation has a problem if it is used because the trailing
edge is open. To overcome this problem, it is necessary to
modify the equation. It is done by replacing the factor of x4
The equation of that angle is:
" d(y /l) %
ϑ =tan -1 $ c '
# d(x/l) &
(6)
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3
B. The transpositions of the airfoil to the stagger angle into
developed plane
There are 2 steps in the transpositions the airfoil to the
stagger angle into developed plane: the translation of the
coordinate system origin in the blade spindle axis and the
rotation around the blade spindle axis until the stagger angle is
reached [2]. The translation of the coordinate system origin in
the blade spindle axis is illustrated in Fig. 4. The blade spindle
axis center in x axis to be xspindle/l=0.3 because in that point,
the airfoil has the maximum thickness [2]. The relations used
for this translation is:
Fig. 2 NACA 6421
with
x ' = x - (xspindle / l) l
(13)
0≤ x< L/l
y ' = y - ( yspindle / l) l
(14)
d( yc / l)
2m / l ⎛ L x ⎞
=
⎜ - ⎟
d(x / l) (0≤x<L/l ) ( L / l)2 ⎝ l l ⎠
(7)
(15)
xspindle / l = 0.3
!
m / l # L xspindle
yspindle / l =
2
( L / l)2 # l l
"
L / l ≤ x ≤1
d( yc / l)
2m / l ⎛ L x ⎞
=
⎜ - ⎟
d(x / l) ( L/l≤x≤1) (1- L / l)2 ⎝ l l ⎠
With
2
!x
$
- ## spindle &&
" l %
$
&
&
%
(16)
(8)
Based on Fig.2, equations required for generating points of the
airfoil can be derived as follow.
"x y
%
xu = $ - t sinϑ ' l
#l l
&
"y y
%
yu = $ c + t cosϑ ' l
l
l
#
&
"x y
%
xl = $ + t sinϑ ' l
#l l
&
⎛y y
⎞
yl = ⎜ c - t cos ϑ ⎟ l
⎝ l l
⎠
(9)
(10)
Fig. 4 Translation of the coordinate system origin in the blade spindle axis
(11)
(12)
The illustration in Fig. 5 describes the process of the rotation
around the blade spindle axis until the stagger angle is
reached. The formulations for this rotation is:
(17)
X = −x 'cos( β c ) + y 'sin( β c )
∞
Those points can be used to draw a profile of an airfoil in
the plane. However airfoil profiles in the formation of the
blade profiles are not drawn in some certain planes but it is
formed from several airfoil profiles on some of the cylinder
surfaces. So the next steps need to be done in order to do the
transformation.
c
∞
Y = −x 'sin( β∞ ) − y 'sin( β∞ c )
(18)
Fig. 5 Rotation around the blade spindle axis until the stagger angle is reached
Fig. 3 Drawing the airfoil profile on the plane
C. The transposition of the airfoils from plane on the
computing cylindrical surfaces
In this step, the airfoil is transposed from its plane to its
cylindrical surface. The initial data for this transposition are
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the coordinates (X, Y) of the transposed profile at the stagger
angle β∞c in the developed plane. So, the current coordinates
of the cylindrical coordinate system are (R, θ, Z) [2]. The
illustration of this step is in Fig. 6. The equations used for this
transposition is:
dsec x
2
2X
θ=
dsec x
R=
Z =Y
(19)
(20)
4
•
•
•
•
•
•
•
m/l to m_l_sec0
L/l to L_l_sec0
t/l to t_l_sec0
β∞c to beta_sec0
l to l_sec0
x to t
x_spindle_sec0 for the position of center in x
direction
Notepad could be used to do the process of code
generation, because it is available in every computer that is
installed with Windows Operating System.
(21)
Fig. 7 Tool parameters of 3-D Equation Curve
Fig. 6 Transposition of the airfoils from plane on the computing cylindrical
surfaces
III. UTILIZING THE 3-D EQUATION CURVE IN AUTODESK
INVENTOR 2015
The process for modeling in Autodesk Inventor 2015 using
3-D Equation Curve can be summarized into the following
steps:
• Generating the code for the Equation Curve
Ø Transforming the geometrical characteristics
variables to tool parameters
Ø Preparing the equations of the airfoil in tool
parameters
Ø Translating the coordinate system origin in the
blade spindle axis
Ø Rotating around the blade spindle axis until the
stagger angle is reached
Ø Transposing the airfoils from plane to the
computing cylindrical surfaces
• Using the Equation Curve for sketching the airfoil
profile
• Creating the blade surfaces
• Creating the solid model of the blade
• Creating the solid model of the runner
A. Transforming the geometrical characteristics variables to
tool parameters.
In order to use the 3-D Equation Curve tool in Autodesk
Inventor 2015, the user needs to define the variables of the
equation. For the case of modeling the runner, the geometrical
characteristics in Table 1 must be transformed to parameters
known to Inventor. For example, it is necessary to change the
variables for section 0 as follow:
• dsec to d_sec0
B. Preparing the equations code of airfoil for section 0
The tool parameters are then used to make the code for
sketching the NACA Airfoil 4 Digit Series in the developed
plane.
Fig. 8 Thickness distribution of NACA airfoil 4 digit series
Fig. 9 Mean lines of NACA airfoil 4 digit series
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The code for thickness distribution is generated from
Equation (3). Then, prepare the mean line equations code from
Equation (4), (5), (7), and (8).
To generate the code for the airfoil profile, the equations
(9) to (12) can be used. There will be 4 line equations code
consisting of: Line 1 (xu, yu at 0<t≤L/l) code, Line 2 (xu, yu
at L/l≤t≤1) code, Line 3 (xl, yl at 0<t≤L/l) code, and Line 4
(xl, yl at L/l≤t≤1) code. The procedure for creating Line 1
code are: use the equations code of xu and yu, replace the yt/l
with yt/l as in Fig.8, replace the d(yc/l)/d(x/l) with
d(yc/l)/d(x/l) from Fig.9 at 0<t≤L/l, and finally replace yc/l
with yc/l from Fig.9 at 0<t≤L/l. Repeat the process for other
lines with their respective range of d(yc/l)/d(x/l) and yc/l. The
result is shown in Fig. 11.
5
Fig. 12 Translating the coordinate system origin in the blade spindle axis
process
Repeat the procedure for the other Lines at other ranges. So
there will be 4 Lines for each section: two lines for range
0<t≤L/l and two lines for range L/l≤t≤1.
Fig. 10 Combining mean lines and thickness distribution of NACA airfoil 4
digit series
Fig. 13 Translating the coordinate system origin in the blade spindle axis code
(1)
Fig. 11 NACA airfoil 4 digit series airfoil code
C. Translating the coordinate system origin in the blade
spindle axis
The transformation (translation) process in code generation
is done by using the equations (13) and (14). For the
coordinate of the spindle axis, use equation (15) and (16).
The procedure (for example the Line 1) is as follows: use
the equations x’ and y’, replace the x and y with xu and yu
respectively (from airfoil) at range 0<t≤L/l, replace xspd in x’
equation with xspd below the y’ equation, replace yspd in y’
equation with yspd below the xspd equation. The x’, y’ are
renamed as xu’ and yu’ at range 0<t≤L/l.
Fig. 14 Translating the coordinate system origin in the blade spindle axis code
(2)
D. Rotating around the blade spindle axis until the stagger
angle is reached
The equations that are used to transform (rotating) the
previous code are the Equation (17) and (18), as it is shown
below (Fig. 15).
The procedure (for example the Line 1) is as follows: use
the equations X and Y, replace x’ in X and Y equation with
xu’ at range 0<t≤L/l, replace x’ in X and Y equation with yu’
at range 0<t≤L/l. The X, Y will be renamed as Xu and Yu at
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6
range 0<t≤L/l. Repeat the procedure for the other Lines at
other ranges. So there will be 4 Lines for each section: two
lines for range 0<t≤L/l and two lines for range L/l≤t≤1.
Fig. 18 Rotating around the blade spindle axis until the stagger angle is
reached code (3)
Fig. 15 Rotating around the blade spindle axis until the stagger angle is
reached process
E. Transposing of the airfoils from plane on the computing
cylindrical surfaces
The last step is to build the code for Equation Curve. In
this last step the previous 2-D cartesian coordinate system is
transformed into 3-D cylindrical coordinate system. The
equations used to transform the code are Equation (18) to (20),
as shown below (Fig. 19).
Fig. 16 Rotating around the blade spindle axis until the stagger angle is
reached code (1)
Fig. 19 Transposing of the airfoils from plane on the computing cylindrical
surfaces process
Fig. 17 Rotating around the blade spindle axis until the stagger angle is
reached code (2)
Fig. 20 Transposing of the airfoils from plane on the computing cylindrical
surfaces code (1)
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Fig. 21 Transposing of the airfoils from plane on the computing cylindrical
surfaces code (2)
The procedure (for example the Line 1) is as follows: use
the equations R, T, and Z replace X in T equation with Xu at
range 0<t≤L/l, replace Y in Z equation with Yu’ at range
0<t≤L/l. The R, T, and Z will be renamed as Ru, Tu, and Zu at
range 0<t≤L/l. Repeat the procedure for the other Lines at
other ranges. So there will be 4 Lines for each section: two
lines for range 0<t≤L/l and two lines for range L/l≤t≤1.
7
Fig. 23 Define the variables in parameters
Subsequently, input the value of these variables based on
Table 1. Repeat this process for other sections by changing the
“sec0” with its respective section such as “sec1” for section 1.
Line 3
Line 1
Line 4
Line 2
Fig. 24 Create the sketch using Equation Curve in 3-D Sketch
Fig. 22 Projected airfoil (3)
F. Using the Equation Curve for sketching the airfoil profile
The code that has been made must be inputted to Equation
Curve. In order to make the tool to recognize the code, the
variables of the code must be defined in the Inventor tool
called Parameters. For example, the variables for section 0
have to be defined in Parameters as follows:
•
•
•
•
•
•
•
d_sec0 use the unit mm
m_l_sec0 use the unit ul
L_l_sec0 use the unit ul
t_l_sec0 use the unit ul
beta_sec0 use the unit deg
l_sec0 use the unit mm
x_spindle_sec0 use the unit ul
After that, input the code in Equation Curve tool at 3-D
Sketch with the coordinate type as cylindrical. For example to
create the Line 1 for section 0: input the Ru from the notepad
at the range 0<t≤L/l to r(t), input the Tu from the notepad at
the range 0<t≤L/l to θ(t), and input the Zu from the notepad at
the range 0<t≤L/l to z(t). Repeat this process for other lines in
section 0. The result would be in Fig. 24.
G. Creating the blade surfaces
The blade is formed by 6 blade profiles. After creating the
first airfoil for section 0 (Fig. 24) the other profiles can be
generated using the code that was made previously (R, T, and
Z) and input the code to Equation Curve. For example, to
create the profile in section 1, change the “sec0” with “sec1”.
Repeat this process for other profiles in other sections. The
surfaces are: pressure side surface, suction side surface, hub
side surface, and shroud side surface.
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8
I. Create the solid model of the runner
There are 7 blades in the runner. The Pattern command can
be used to copy the blade. The direction of pattern is circle
(across the hub).
Fig. 25 Profiles of the blade
The creation of the blade surfaces has been done using 2
following commands: Boundary Patch and Loft. The boundary
patch is used twice: creating the shroud side surface by using
the section 0 profile and the hub side surface by using the
section 5. The loft command (surface type) is used to create
the pressure side and suction side surfaces.
Fig. 28 Blades pattern
Hub Side
Pressure Side
Shroud Side
Suction Side
Fig. 26 Surfaces of the blade
H. Create the solid model of the blade
From the surfaces that have been made, solid model of the
blade can be generated, using Stitch command. For the
purposes of meshing, in the next step fillet should be given to
the trailing edge.
Fig. 29 Solid model of the runner
IV. ANALYSIS OF THE SOLID MODEL OF THE RUNNER
CFD (Computational Fluid Dynamics) is used for
analyzing the performance of the designed blade and runner
numerically. There are two steps of analyzing the model:
meshing the model and simulating it as follows:
A. Mesh the model with Gambit
To simulate the runner model in CFD, the fluid
surrounding the runner should be modeled (Fig. 30), before
exporting it to Gambit.
Fillet
Fig. 27 Solid model of the blade
Fig. 30 Negative model of the runner
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9
•
The SIMPLE scheme and Gradient are used as GreenGauss Node Based [9].
• The Initialization type is used as Hybrid Initialization
[10].
After the simulation set the following boundary
condition for Turbo Topology [11]:
• Runner_Inlet as Inlet
• Runner_Outlet as Outlet
• Runner_Hub as Hub
• Runner_Case as Case
• Runner_Blades as Blade
• Default-Interior as Theta Periodic
The hydraulic efficiency reported by Turbo Topology is 85.45
%.
Fig. 31 The mesh of the runner
The negative model is created by subtracting the cylinder with
a height equal to the height of the runner and a diameter equal
to the diameter of the runner with the model of the runner.
The negative model is then exported to Gambit in ACIS
format file (.sat). Set the boundary conditions as follow:
• On the inlet surface use Pressure Inlet and give the name
Runner_Inlet.
• On the outlet surface use Pressure Outlet and give the
name Runner_Outlet.
• On the hub surface use Wall and give the name
Runner_Hub.
• On the case surface use Wall and give the name
Runner_Case.
• On the blades surface use Wall and give the name
Runner_Blades.
Set the Continuum type of the model as Fluid. Mesh the
model with hexahedral volume element and Cooper type.
Hexahedral is chosen because of its accuracy [6]. The number
of element is 53000.
B. Model simulation using ANSYS Fluent
The simulation has to be set at the design condition of the
runner. The runner is designed for Head = 7 m, flowrate = 0.5
m3/s, and rotational speed = 750 rpm. The following setup has
been done before running the simulation using the ANSYS
Fluent:
• The viscous is set to k-epsilon standard [7].
• The material type is set to water fluid.
• The cell zone condition is set to frame motion with
rotation velocity is 750 rpm with z as rotation axis [8].
• Boundary conditions are set as follow:
Ø Runner_Inlet as Pressure Inlet with Gauge Pressure
68532 Pa (Head=7 m).
Ø Runner_Outlet as Pressure Outlet with Gauge
Pressure 0 Pa.
Ø Runner_Hub and Runner_Blades as Moving Wall
with Rotation as moving type and relative to adjacent
cell.
Ø Runner_Case as Stationary Wall.
Fig. 32 The hydraulic efficiency of the runner
V. CONCLUSION
•
•
Propeller water turbine runner could be modeled using
Autodesk Inventor 2015 using 3-D Equation Curve.
The simulation shows that the efficiency of the runner
is quite satisfactory.
REFERENCES
[1]
[2]
[3]
[4]
[5]
D. Nedelcu, I. Padurean, “CAD Modelling of Axial Blade Turbine using
Autodesk Inventor”, Scientific Bulletin of the Politechnica University
Timisoara, Romania, ISSN 1224 – 6077, No. 1, 2007
T. Milos, M. O. Popoviciu, I. Bordeasu, R. Badarau, A. Bej, and D.
Bordeasu, “The 3d blade surface generation for kaplan turbines using
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fine.html
Indra Djodikusumo was born in Bondowoso, East Java,
Indonesia at the 18th of January 1955. He received his
Bachelor’s Degree from Institute of Technology Bandung,
Faculty of Mechanical and Aerospace Engineering, in 1978 in
the field of Production Engineering. He got his Masters
Degree of Mechanical Engineering in 1981 in Katholieke
Universiteit Leuven Belgium in the field of Production
Engineering and his Doctoral’s Degree in Engineering in 1994
in the Technical University Berlin in the field of System
Planning.
He has been a Lecturer at the Faculty of Mechanical and
Aerospace Engineering, the Institute of Technology Bandung
from 1978 to present. The first author is an active member of
the Association of Hydro Bandung, and the technical member
of Indonesian National Standard in the field of Microhydro.
He has invented patent for silent chains of the timing chains in
motorcycle’s internal combustion engines that are now already
manufactured in mass production scale for after market in
Indonesia. Some of his works are:
• Tolerance Stack Analysis in Francis Turbine Design,
Journal of Engineering and Tecnological Sciences,
Institute of Technology Bandung, 2010.
• Design, 3-D Modeling and Simulation of Propeller
Turbine Runner Utilizing NACA Profile, currently
being reviewed at the Journal of Engineering and
Tecnological Sciences in Institute of Technology
Bandung.
• A book entitled Guideline of Designing the Runner
for a Propeller Turbine, which will be published very
soon.
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His research projects were in the fields of automotive
components, micro- and mini hydro turbine and agricultural
post harvesting machineries. His research focus is in the field
of Reverse Engineering.
I Nengah Diasta was born in Bali, Indonesia, in 1965. He
received the B.S Degree in 1991 and M.S. Degree in 1997
from Faculty of Mechanical Engineering and Aerospace
Institute of Technology Bandung, Indonesia.
He has been an Expert Research Assistant in Fluid
Mechanic Laboratory in Institute of Technology Bandung
since 1994. The second author participated in various seminars
and conferences related to turbo machinery. Some of his
recent publications are:
• Simulation and Investigation of the Air-Foil Motion
in the Extremely Low Head Ducted Darrieus Type
Water Turbine (RCNRE 2012) and
• Quasi 3-D Inverse Design Method, Optimization
Criterion for Very Low Head Axial Turbine Design
(FTEC 2011).
His research interests include: fluid mechanics and fluid
machinery.
Fachri Koeshardono was born in Bandung, West Java,
Indonesia in 1990. He received the B.S and M.S. degrees in
mechanical engineering from the Institute of Technology
Bandung in 2015.
From 2012, he has been a Research Assistant in Mechanical
Production Engineering Laboratory. He is the author of paper
entitled “Kaji Konservasi Energi Pemanfaatan Panas Limbah
Proses Dyeing, Drying, and Stentering Pabrik Tekstil”. His
research interests include textile process, Microhydro turbine,
CAD modelling, and reverse engineering.