Preliminary engine Design GasTurb 13 Preliminary engine Design Copyright © GasTurb GmbH

For this tutorial we will use a Turbojet GasTurb 13 Main Window For this tutorial we will use a Turbojet and the scope More… Copyright © GasTurb GmbH

Select the engine model We Need Some Data Select the engine model Open the engine model Copyright © GasTurb GmbH

There are two more buttons with this scope Input Data Page Click on Edit Geometry Copyright © GasTurb GmbH There are two more buttons with this scope

General Arrangement Copyright © GasTurb GmbH

General Arrangement Copyright © GasTurb GmbH

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. Copyright © GasTurb GmbH By selecting “Show Disk Mass”, the masses will be displayed in the drawing

General Arrangement Copyright © GasTurb GmbH If you select “Measure” zooming will be disabled and you can measure distances and angles of your design Copyright © GasTurb GmbH

Inlet Design Options (1) Input Output Strut/Chord Height = 0.5 Strut/Chord Height = 1 Copyright © GasTurb GmbH

Inlet Design Options (2) Strut/Chord Height = 0.5 Cone Angle = 10° Number of Struts=0 Cone Angle = 25° Cone Length/Radius = 0.1 Copyright © GasTurb GmbH Strut/Chord Height = 0.5 Cone Angle = 30° Number of Struts=0 Cone Angle = 35° Cone Length/Radius = 1.3

Compressor Design Options Input Output Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

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

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.

Compressor Length Aspect Ratio = 1.5 Aspect Ratio = 2 Copyright © GasTurb GmbH

Compressor Annulus Copyright © GasTurb GmbH Here you can get a detailed overview of the compressor annulus geometry Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

Burner Input Output Compressor Input The diffusor area ratio is an input on the HP compressor input page Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH Exit/Inlet Radius = 1.3 Length/Inlet Radius = 1.5

Turbine Design Shrouded Un-Shrouded Copyright © GasTurb GmbH Input Output Shrouded Un-Shrouded Copyright © GasTurb GmbH

Turbine Flow Annulus Aspect Ratio (Span/Chord) = 1.2 Inner Radius: R,exit/R,inlet = 0.97 Inner Annulus Slope @ Inlet = 0° Inner Annulus Slope @ Exit = -10° Aspect Ratio = 1.5 Inner Annulus Slope @ Inlet = 10° +10° Inner Annulus Slope @ Exit= 10° +10° Inner Radius: R,exit/R,inlet = 0.9 Copyright © GasTurb GmbH

Turbine Exhaust Chasing Input Output Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH Cone ends in the exhaust duct Cone continues in nozzle Cone Length/Inlet Radius = 0.95

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

Plug Nozzle Input Output Copyright © GasTurb GmbH

Power Generation Exhaust Input Output Copyright © GasTurb GmbH

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. Copyright © GasTurb GmbH

Bypass Input Output Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

Disk Nomenclature Copyright © GasTurb GmbH Hyperbolic disk Web disk

Disk Design Data Copyright © GasTurb GmbH To access the disk design select any component that includes disks Click on “Disk” to perform disk calculations Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

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. Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

Blade Attachment Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

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 Copyright © GasTurb GmbH

Disk Stress Details An Option in GasTurb Details 6 Copyright © GasTurb GmbH

Material Data Bank Editor A Feature of GasTurb Details 6 Copyright © GasTurb GmbH