BLADE3DR - turboaerodesign.comBlade three-dimensional profile design and aero/hydrodynamic analysis...
Transcript of BLADE3DR - turboaerodesign.comBlade three-dimensional profile design and aero/hydrodynamic analysis...
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BLADE3DRVersion 3.3
2018
Dr. Justin (Jongsik) Oh
www.TurboAeroDesign.com
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INTRODUCTIONBLADE3DR ver. 3.3
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Blade three-dimensional profile design and aero/hydrodynamic analysis in turbomachinery
A single row blade
Design parameters
Hub and shroud contours
Blade camberline metal angle
Blade normal thickness
Aerodynamic analysis options
Blade loading analysis• SCM (Streamline Curvature Method, or Velocity Gradient Method)
• FEM (Finite Element Method)
Blade 3D simplified CFD• Explicit time-marching method using body forces for turbulent viscous terms
• No rotor tip clearance
• Real gas option included
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Development was motivated by personal needs for Better Performance and Reliability at aero design tasks since 2002 while using some commercial software, including
CCAD (by Concepts ETI, but now Concepts NREC)
COMIG (by NREC, but now gone)
BladeGen and BladeGenPlus (by AEA Technology)
AxCENT (by Concepts NREC)
BladeModeller (by Ansys)
Over 12 year-use in personal aero-design tasks at various applications, still evolving.
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Program Strucuture Windows-based ( FORTRAN + Visual Basic ) Aiming for use of PC or laptops Programs are installed in “C:\OJS\TurboSW\Blade3DR\Ver3_3\”. All input/output files are located in “C:\OJS\TurboSW\Blade3DR\Ver3_3\Work\”. All input/output file names are pre-determined and fixed. When tasks are done, all necessary files should be copied to the local folder using the data management menu.
Program Limits A single row of blades Max. two-row tangential splitter blades No fillets Currently limited CAD export options (DXF and STL) *
Program Plus Capabilities Two different methods for blade loading analysis (SCM + FEM) 3D compressible or incompressible turbulent CFD Blade rotation by specified angle (useful for IGV model) Large single screen for better work performance (that I love) Supplementary viewer + Text viewer Total 21 spanwise uniformly-spaced layers (fixed) Two curve options
• Spline **
• Bezier polynomial
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(*) When professional s/w expertise is added,it will be extended to IGES and STEP, etc.However, a solid can be easily created fromSTL with any CAD programs.
(**) In some situation, using Spline providesbetter work performance than Bezier. You willneed both.
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• Large single screen for edit
• Supplementary viewer
• Text viewer
• Easy-access buttons
• File inputs
.rtzt
.ojs
.curve
Meanline output from
all my design programs
The .rtzt file is of a blade meanline format,
shared with all my programs and also with Ansys
BladeModeller (See Appendix).
The .ojs file is of directly-saved data of Blade3D.
The .curve files are Ansys Turbogrid inputs.
Just for illustration (of arbitrary design) to show capabilities of two-row splitters with real gas
Centrifugal compressor impeller using HFC-134a refrigerant
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• 2D DXF
• 3D DXF wireframe
• 3D STL
• Direct inputs for
Ansys Turbogrid (.curve)
Numeca FineTurbo (.geomturbo)
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Dynamic View
Spanwise Distributions
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• Various setting options for
better design performance
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• Various edit options for
better design performance
Spline
Bezier Polynomial
• BETA or THETA edit
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• Various edit options for better design performance
• Edit while looking at hub and shroud curves together
• By default, all tangential splitter-blades follow full-blade
angles. However, they can be changed via Option menu.
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• Edit while looking at hub and shroud curves together
• All tangential splitter-blade thicknesses are independently
changeable.
• Sometimes “spline” curve is better than “Bezier polynomial” at
heavy rate of changes in the distribution. You will need both.
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• Total 5 Options
Circle
Ellipse
Bezier *
Pseudo *
Cut-off
(*) In case that the ellipse approach fails
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• Unusual case, but available
Through an add-on editor
• Example shows the change of
BETA of 2nd-row splitter.
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• Unusual case, but available
Through an add-on editor
• Example shows the change of
THETA of 1st-row splitter.
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• Blade trim or extension
Impeller outer diameter
o on hub
o on shroud
Impeller exit height
Impeller inlet height
• While reserving baseline shape of
Blade angle
Blade thickness
• Useful option for industry design needs
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• Two Different Analysis Methods
SCM (Streamline Curvature Method)
o Also called Velocity Gradient Method
o Sove the velocity gradient equation (inviscid) along
each quasi-orthogonal to streamlines from inlet to exit
FEM (Finite Element Method)
o Subsonic stream-function Poisson equation (inviscid)
o Adler & Krimerman’s H-S stream surface approach
Ideal gas or incompressible fluid for both methods
Note : Just for illustration to show capabilities of two-row splitters with real gas
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Streamlines after
solution converges
Again, just for illustration to show capabilities of two-row splitters with real gas
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Streamlines after
solution converges
The FEM program is a part of my
Ph.D. thesis achievements (1992).
Streamlines after
solution converges
Again, just for illustration to show capabilities of two-row splitters with real gas
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• A single blade row
• Compressible fluid
Ideal gas
Real gas
• Incompressible fluid
• Turbulent viscous body forces
• No rotor tip clearance
• Multi-grid convergence
• Structured grids
• Effective tool to check aero designs
Again, just for illustration to show capabilities of two-row splitters with real gas
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Again, just for illustration to show capabilities of two-row splitters with real gas
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Again, just for illustration to show capabilities of two-row splitters with real gas
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Again, just for illustration to show capabilities of two-row splitters with real gas
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• Example using FreeCAD
Part environment
Open > Blade3D.STL
Part > Creat shape from mesh
Blade3D001 solid
with spanwise extensions
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• Tangential Lean
Edit stacking curve
Mostly axial blades
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• Meridional Sweep
Edit stacking curve
Mostly axial blades
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• Interstage key component
Sample industry design from
a multistage centrifugal chiller
compressor using HFC-134a,
looking a lot problematic in
aerodynamics
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On mid-pitchOn 75% span from hub
Near trailing-edge
Blade loadings on shroud
FEMSCM
FEM
Streamlines
SCM
streamlines
Blade Loading Analysis
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• CFD inputs
• Real gas
• 0 rpm (stationary)
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On mid-pitchOn 75% span from hub
Near trailing-edge
Blade loadings on shroud
Spanwise flow angles
at discharge
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• Conventional water
pump impeller
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Loading
Analysis
FEMSCM
FEM
StreamlinesSCM
streamlines
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• CFD inputs
• Incompressible fluid
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• Time-marching
method using
artificial
compressibility for
incompressible
fluid simulation
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On Shroud
On mid-pitch On mid-span
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• Radial-inflow
turbine rotor with
one-row splitter
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FEM
SCM
FEM
Streamlines
SCM
streamlines
Loading Analysis
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On lower mid-pitch
On 75% span from hub
Secondary flows
near trailing-edge
On shroud
• CFD
• Transonic rotor
Convergence
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• NASA CR 72562
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• CFD results
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APPENDIX
BLADE3DR ver.3.3
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• One of Blade3DR default input formats
Blade meanline geometry
Originally the format was from BladeGen (AEA Technology). (now Ansys BladeModeller)
However, for tangential splitter blades, Blade3DR uses a different definition of pitchwise locations.
Full-blade count Number of tangential splitter blades
Full-blade pitch position Number of spans N (Normal thickness) M
T (Tangential thickness)
Normalized span from hub Total number of data
R (Radius) Theta (rad) Z (Axial) T (Thickness)
along camberline
from bladeless-upstream, blade and bladeless-downstream
Normalized span from hub Total number of data
R (Radius) Theta (rad) Z (Axial) T (Thickness)
along camberline
from bladeless-upstream, blade and bladeless-downstream
>
>
>
○○ Repeated to Shroud
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End of bladeless-downstream at shroud of full blade
1st-row splitter pitch position(*) Number of spans N (Normal thickness) M
T (Tangential thickness)
Normalized span from hub Total number of data
R (Radius) Theta (rad) Z (Axial) T (Thickness)
along camberline
from bladeless-upstream, blade and bladeless-downstream
Normalized span from hub Total number of data
R (Radius) Theta (rad) Z (Axial) T (Thickness)
along camberline
from bladeless-upstream, blade and bladeless-downstream
>
>
○○ Repeated to Shroud
>
(*) Relative pitch between two adjacent full blades
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End of bladeless-downstream at shroud of 1st-row splitter blade
2nd-row splitter pitch position(**) Number of spans N (Normal thickness) M
T (Tangential thickness)
Normalized span from hub Total number of data
R (Radius) Theta (rad) Z (Axial) T (Thickness)
along camberline
from bladeless-upstream, blade and bladeless-downstream
Normalized span from hub Total number of data
R (Radius) Theta (rad) Z (Axial) T (Thickness)
along camberline
from bladeless-upstream, blade and bladeless-downstream
>
>
○○ Repeated to Shroud
>
(**) Relative pitch between full blade and 1st-row splitter blade
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