1. Preliminary engine Design
GasTurb 12
Preliminary engine Design
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2. For this tutorial we will use a Turbojet
GasTurb 12 Main Window
For this tutorial we will use a Turbojet
and the scope
More…
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3. Select the engine model
We Need Some Data
Select the engine model
Open the engine model
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4. There are two more buttons with this scope
Input Data Page
Click on
Edit Geometry
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There are two more buttons with this scope

5. General Arrangement
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6. Inlet Design Options (1)
Strut/Chord Height = 0.5
Strut/Chord Height = 1
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7. Inlet Design Options (2)
Strut/Chord Height = 0.5
Cone Angle = 10°
Number of Struts=0
Cone Angle = 25°
Cone Length/Radius = 0.1
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Strut/Chord Height = 0.5
Cone Angle = 30°
Number of Struts=0
Cone Angle = 35°
Cone Length/Radius = 1.3

8. Compressor Design Options
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9. Compressor Flow Annulus Shape
Annulus Shape Descriptor = 1
Annulus Shape Descriptor = 0.5
Inlet Radius Ratio is calculated during cycle design in this example
Annulus Shape Descriptor = 0
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10. Compressor Length Aspect Ratio = 1.5 Aspect Ratio = 2
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11. Interactive Design See how an input quantity affects the design
Select a quantity
Click on
Slider Control
Adjust min and max value and click OK
Choose quantity from the list
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12. Burner
The diffusor area ratio is an input on the HP compressor input page
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13. Burner Shape Can Width/Length = 0.4 Can Width/Length = 0.6
Length/Inlet Radius = 1
Exit/Inlet Radius = 1.1
Can Width/Length = 0.6
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Exit/Inlet Radius = 1.3
Length/Inlet Radius = 1.5

14. Turbine Design
Shrouded
Un-Shrouded
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15. Turbine Flow Annulus Aspect Ratio (Span/Chord) = 1.2
Inner Radius: R,exit/R,inlet = 0.97
Inner Annulus Inlet = 0°
Inner Annulus Exit = -10°
Aspect Ratio = 1.5
Inner Annulus Inlet = 10°
+10°
Inner Annulus Exit= 10°
+10°
Inner Radius: R,exit/R,inlet = 0.9
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16. Turbine Exhaust Chasing
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17. Turbine Exhaust Flow Annulus
Cone Angle = 19°
Casing Length/Inlet Radius = 1
Cone Length/Inlet Radius = 0.5
Cone Angle = 30°
Casing outer exit radius moves because A6 is retained
Cone Length = 0
Cone Length/Inlet Radius = 1 A6 A6
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Cone ends in the exhaust duct
Cone continues in nozzle
Cone Length/Inlet Radius = 0.95

18. Standard Convergent Nozzles
Turbine Exhaust Cone ends in nozzle
Turbine Exhaust Cone continues in nozzle
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Petal angle is input on the Nozzle Calculation page (cycle design)

19. Plug Nozzle
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20. Power Generation Exhaust
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21. Interduct
The inner contour of the flow annulus is described with a 3rd order polynominal with given slopes at the inlet and the exit of the duct.
The outer contour follows from a linear area change from the inlet to the exit of the duct.
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22. Bypass
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23. Bypass Shape Copyright © GasTurb GmbH
Flat Point Radius/Inlet Radius = 1,27
Flat Point Radius/Inlet Radius = 1,37
Flat Point Radius/Inlet Radius = 1,27
Flat Point Position = 40% of Length
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24. Bypass with Struts
Nozzle position is measured relative to inner bypass length (Station 13 → Station 5)
Strut position is measured relative to outer bypass length (Station 13 → Station 16)
Outer Bypass Length
Inner Bypass Length
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25. Disk Nomenclature
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Hyperbolic disk
Web disk

26. Disk Design Data Copyright © GasTurb GmbH Free disk input Result
Calculated disk input
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Input for minimum disk bore radius - applied to all disks

27. Disk Design Data Copyright © GasTurb GmbH
Equal to the temperature difference from the platform to the center point of the disk.
Disk shape optimization options
Disk design criteria
Blades are modeled as plates
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Material selection

28. Blade Attachment
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29. Stress Adaptation Options Optimization Off
Adapt Bore Width = 0
bore width is as given by input
Adapt Bore Width = 1
bore width is adapted to the target design stress margin
Adapt Bore Radius = 0
Adapt Bore Radius = 1
bore radius is as given by input
bore radius is adapted to the target design stress margin
bore radius is set to its
lower limit
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30. Stress Adaptation Options Optimization On
Optimization Variables
lower limit
upper limit
Outer Rim Height/Rim Width
0.1 1
Web Width/Rim Width
0.15
Inner Rim Height/Rim Width
0.2
Figure of Merit = Weight
Constraint = All Design Margins >= 0
Adapt Bore Width = 0
bore width is as given by input
Adapt Bore Width = 1
bore width is an optimization variable
Adapt Bore Radius = 0
Adapt Bore Radius = 1
bore radius is as given by input
bore radius is an
optimization variable
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31. Disk Calculation Options
Here you can control optimization of each disk individually.
Overstressed disks are displayed yellow.
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32. Disk Stress Details An Option in GasTurb Details 6
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33. Material Data Bank Editor A Feature of GasTurb Details 6
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