1. Preliminary engine Design
GasTurb 13
Preliminary engine Design
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2. For this tutorial we will use a Turbojet
GasTurb 13 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. General Arrangement
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7. Select the component you want to design
General Arrangement
Select the component you want to design
For each Component the Input and output is listed in the corresponding Tab
If you deselect “Show Axis”, by pressing Control you will be able to move the Drawing with your mouse in a drag and drop way.
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By selecting “Show Disk Mass”, the masses will be displayed in the drawing

8. General Arrangement Copyright © GasTurb GmbH
If you select “Measure” zooming will be disabled and you can measure distances and angles of your design
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9. Inlet Design Options (1)
Input
Output
Strut/Chord Height = 0.5
Strut/Chord Height = 1
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10. 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

11. Compressor Design Options
Input
Output
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12. 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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13. Compressor Flow Annulus Shape
The compressor annulus shape can also be altered in the control panel. Different modes are offered:
Simple: define the shape descriptor
Bézier: use a Bézier curve to define the shape
Sketch: use a Bézier curve to define the shape. Additionally you may define blade geometry for each stage

14. Compressor Flow Annulus Shape
By selecting “Show Disk Mass”, the masses will be displayed in the drawing
If you deselect “Show Axis”, by pressing Control you will be able to move the Drawing with your mouse in a drag and drop way.

15. Compressor Length Aspect Ratio = 1.5 Aspect Ratio = 2
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16. Compressor Annulus Copyright © GasTurb GmbH
Here you can get a detailed overview of the compressor annulus geometry
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17. Interactive Design See how an input quantity affects the design
Select a quantity
Adjust min and max value and click OK
Click on
Slider
Choose quantity from the list
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18. Burner
Input
Output
Compressor Input
The diffusor area ratio is an input on the HP compressor input page
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19. 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

20. Turbine Design Shrouded Un-Shrouded Copyright © GasTurb GmbH Input
Output
Shrouded
Un-Shrouded
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21. 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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22. Turbine Exhaust Chasing
Input
Output
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23. 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

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

25. Plug Nozzle
Input
Output
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26. Power Generation Exhaust
Input
Output
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27. Interduct
Input
Output
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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28. Bypass
Input
Output
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29. 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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30. Bypass with Struts
Input
Output
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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31. Disk Nomenclature
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Hyperbolic disk
Web disk

32. Disk Design Data Copyright © GasTurb GmbH
To access the disk design select any component that includes disks
Click on “Disk” to perform disk calculations
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33. Overstressed disks are displayed yellow.
Disk Design Data
Here we can select the stage we want to work on and define a material for each stage.
An Optimization of each individual stage is possible and is controlled here.
Overstressed disks are displayed yellow.
Just like in the geometry design window, Input, calculated Boundary Conditions and Output of each disk can be accessed here
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34. Disk Design Data Copyright © GasTurb GmbH Input Calculated Input
Output
The lower limit of the bore radius is defined in the geometry design of the corresponding component.
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35. 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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36. Blade Attachment
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37. 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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38. 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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39. Disk Stress Details An Option in GasTurb Details 6
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40. Material Data Bank Editor A Feature of GasTurb Details 6
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