*TURBINE ROTOR |
 
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*TURBINE ROTOR |
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To assemble a wind turbine rotor by selecting blades and specifying related information.
Refer to Turbine Geometry for further information.
A block comprised of several lines.
Line defining the number of blades:
NUMBER OF BLADES=Number of Blades
Lines selecting the required blade profiles:
BLADE1=Blade 1 Name [, COLOUR=Blade 1 Colour]
[BLADE2=Blade 2 Name] [, COLOUR=Blade 2 Colour]
[BLADE3=Blade 3 Name] [, COLOUR=Blade 3 Colour]
Lines defining the drivetrain torsional spring and damper components:
[DRIVETRAIN SPRING=DTTorSpr]
[DRIVETRAIN DAMPER=DTTorDmp]
Line defining the hub radius:
HUB RADIUS=Hub Radius
Optional line defining the precone angle of the blade:
[PRECONE ANGLE=Precone Angle]
Optional line defining the initial pitch angle of the blade:
[PITCH ANGLE=Initial Pitch Angle]
Optional line defining the inclusion of pitching-moment terms:
[USEBLCM=Include Pitching Moment]
Optional line selecting the blade modelling approach, be it rigid or flexible:
[BLADE MODEL=Blade Model]
Refer to the Turbine Geometry schematics for an illustration of the various inputs. Both Blade 2 Name and Blade 3 Name default to Blade 1 Name if not specified. Precone Angle and Initial Pitch Angle default to 0 degrees if not specified. Set Include Pitching Moment to 1 to include the pitching-moment terms in the blade aerofoil aerodynamics, or 0 (the default) to neglect them. Blade Model can be RIGID or FLEXIBLE.
The rotor is assembled according to the blade selections and related information defined in the *TURBINE ROTOR keyword. Flexcom creates a node in the finite element discretisation corresponding to each blade span position defined in the *BLADE GEOMETRY keyword. These nodes are connected sequentially using finite elements whose structural properties are governed by the inputs in the *BLADE STRUCTURE keyword. The structural properties are assumed constant along each element, and determined using linear interpolation between the element centrepoint and the nearest available sectional definitions.
Input: |
Description |
Number of Blades: |
The number of blades, which can be 1, 2 or 3. |
The name of the first blade. Note that the same blade names should be used in the *BLADE GEOMETRY, *BLADE STRUCTURE and *TURBINE ROTOR keywords. |
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Blade 1 Colour: |
Optional colour to be assigned to Blade 1 elements. See *SET COLOURS keyword for further details. |
Blade 2: |
The name of the second blade. This defaults to the first blade name if not specified. |
Blade 2 Colour: |
Optional colour to be assigned to Blade 2 elements. |
Blade 3: |
The name of the third blade. This defaults to the first blade name if not specified. |
Blade 3 Colour: |
Optional colour to be assigned to Blade 3 elements. |
Drivetrain Torsional Spring: |
The rotational stiffness of the drivetrain torsional spring. This entry controls the torsional stiffness of the shaft element. A rigid shaft is modelled by Flexcom if no rotational flexibility is specified. |
Drivetrain Torsional Damper: |
The rotational stiffness of the drivetrain torsional damper. This entry is currently redundant in Flexcom as the torsional damper elements which simulate the generator torque are controlled by ServoDyn. |
Hub Radius: |
The radius to the blade root from the center-of-rotation along the (possibly preconed) blade-pitch axis. This is illustrated by 'HubRad' in Turbine Geometry and subsequent schematics. |
Precone Angle: |
The angle in degrees between a flat rotor disk and the cone swept by the blades, positive downwind. Upwind turbines have a negative precone angle for improved tower clearance. This is illustrated by 'Precone' in Turbine Geometry and subsequent schematics. |
Pitch Angle: |
The initial blade pitch angle in degrees, positive to feather, leading edge upwind. The axis of rotation is illustrated by 'Blade-Pitch Axis' in Turbine Geometry, while the angle convention is illustrated by 'm: Pitching' in Blade Local Coordinate System. The initial blade pitch angle defaults to 0 degrees if not specified. |
Pitching-Moment: |
This option allows you to include or exclude (the default) pitching-moment terms in the blade aerofoil aerodynamics. |
Blade Model: |
This option allows you to choose between a simplistic rigid or fully flexible model of the rotating blades. Refer to Rotor Blade Model for full details. |
(a)You can define as many blades as you wish in the *BLADE GEOMETRY and *BLADE STRUCTURE keywords. Only the blades which you reference in the *TURBINE ROTOR keyword will be used in the model.
(b)If you have selected the Flexible blade model, Flexcom creates a node in the finite element discretisation corresponding to each blade span position defined in the *BLADE GEOMETRY keyword. These nodes are connected sequentially using finite elements whose structural properties are governed by the inputs in the *BLADE STRUCTURE keyword. The structural properties are assumed constant along each element, and determined using linear interpolation between the element centrepoint and the nearest available sectional definitions.