preliminary engine design gasturb 12 copyright © gasturb gmbh
TRANSCRIPT
![Page 1: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/1.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
PRELIMINARY ENGINE DESIGN
GasTurb 12
![Page 2: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/2.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
GasTurb 12 Main Window
For this tutorial we will use a Turbojet
and the scopeMore…
![Page 3: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/3.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
We Need Some Data
Select the engine model
Open the engine model
![Page 4: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/4.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Input Data Page
There are two more buttons
with this scope
Click onEdit Geometry
![Page 5: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/5.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
General Arrangement
![Page 6: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/6.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Inlet Design Options (1)
Strut/Chord Height = 0.5
Strut/Chord Height = 1
![Page 7: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/7.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Inlet Design Options (2)
Strut/Chord Height = 0.5Cone Angle = 10°
Strut/Chord Height = 0.5Cone Angle = 30°
Number of Struts=0Cone Angle = 25°Cone Length/Radius = 0.1
Number of Struts=0Cone Angle = 35°Cone Length/Radius = 1.3
![Page 8: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/8.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Compressor Design Options
![Page 9: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/9.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Compressor Flow Annulus ShapeIn
let
Rad
ius
Rat
io is
ca
lcul
ated
dur
ing
cycl
e de
sign
in t
his
exa
mpl
e
Annulus Shape Descriptor = 1
Annulus Shape Descriptor = 0.5
Annulus Shape Descriptor = 0
![Page 10: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/10.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Compressor Length
Aspect Ratio = 1.5 Aspect Ratio = 2
![Page 11: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/11.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Interactive DesignSee how an input quantity affects the design
Click onSlider Control
Select a quantity
Choose quantity from the list
Adjust min and max value and
click OK
![Page 12: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/12.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Burner
The diffusor area ratio is an input on the HP compressor input page
![Page 13: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/13.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Burner Shape
Can Width/Length = 0.4Length/Inlet Radius = 1Exit/Inlet Radius = 1.1
Can Width/Length = 0.6
Length/Inlet Radius = 1.5Exit/Inlet Radius = 1.3
![Page 14: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/14.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Turbine Design
Shrouded Un-Shrouded
![Page 15: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/15.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Turbine Flow Annulus
Aspect Ratio (Span/Chord) = 1.2Inner Radius: R,exit/R,inlet = 0.97Inner Annulus Slope @ Inlet = 0°Inner Annulus Slope @ Exit = -10°
Inner Radius: R,exit/R,inlet = 0.9
Aspect Ratio = 1.5
Inner Annulus Slope @ Inlet = 10°
+10°
Inner Annulus Slope @ Exit= 10°
+10°
![Page 16: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/16.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Turbine Exhaust Chasing
![Page 17: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/17.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Turbine Exhaust Flow Annulus
Cone Angle = 19°Casing Length/Inlet Radius = 1Cone Length/Inlet Radius = 0.5
Cone Length/Inlet Radius = 1
Cone Angle = 30°
Cone Length/Inlet Radius = 0.95
Cone Length = 0
Cone ends in the exhaust duct
Cone continues in nozzle
A6
Casing outer exit radius moves because A6 is retained
A6
![Page 18: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/18.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Standard Convergent Nozzles
Turbine Exhaust Cone ends in nozzle
Turbine Exhaust Cone continues in nozzle
Petal angle is input on the Nozzle Calculation page (cycle design)
![Page 19: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/19.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Plug Nozzle
![Page 20: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/20.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Power Generation Exhaust
![Page 21: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/21.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
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.
![Page 22: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/22.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Bypass
![Page 23: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/23.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Bypass ShapeFlat Point Radius/Inlet Radius = 1,27
Flat Point Radius/Inlet Radius = 1,37
Flat Point Radius/Inlet Radius = 1,27Flat Point Position = 40% of Length
![Page 24: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/24.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
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
![Page 25: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/25.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Disk Nomenclature
Web diskHyperbolic
disk
![Page 26: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/26.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Disk Design Data
Free disk input
Result
Calculated disk input
Input for minimum disk bore radius - applied to all disks
![Page 27: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/27.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Disk Design DataEqual 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
Material selection
![Page 28: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/28.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Blade Attachment
![Page 29: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/29.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Stress Adaptation OptionsOptimization Off
Adapt Bore Width = 0bore width is as given by input
Adapt Bore Width = 1bore width is adapted
to the target design stress margin
Adapt Bore Radius = 0 Adapt Bore Radius = 1 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 as given by input
bore radius is set to its lower limit
![Page 30: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/30.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Stress Adaptation OptionsOptimization On
Adapt Bore Width = 0bore width is as given by input
Adapt Bore Width = 1bore width is an optimization variable
Adapt Bore Radius = 0 Adapt Bore Radius = 1 Adapt Bore Radius = 0 Adapt Bore Radius = 1
bore radius is as given by input
bore radius is an optimization variable
bore radius is as given by input
bore radius is an optimization variable
Figure of Merit = WeightConstraint = All Design Margins >= 0
lower limit upper limit
Outer Rim Height/Rim Width 0.1 1
Web Width/Rim Width 0.15 1
Inner Rim Height/Rim Width 0.2 1
Optimization Variables
![Page 31: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/31.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Disk Calculation Options
Here you can control optimization of each disk
individually.
Overstressed disks are displayed yellow.
![Page 32: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/32.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Disk Stress DetailsAn Option in GasTurb Details 6
![Page 33: PRELIMINARY ENGINE DESIGN GasTurb 12 Copyright © GasTurb GmbH](https://reader036.vdocument.in/reader036/viewer/2022081501/56649dbf5503460f94ab30a4/html5/thumbnails/33.jpg)
Cop
yrig
ht ©
Gas
Tur
b G
mbH
Material Data Bank Editor A Feature of GasTurb Details 6