Wind Turbine Blade Segmentation and Flow Control
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Solution Overview
Problem
The traditional design process for wind turbine blades is complex and time-consuming, with high production costs due to the need for intricate aerodynamic shapes and manufacturing processes, which complicates the development and production of new blade types.
Innovation Solution
A modular blade design with a base part having a linearly varying inner dimension, allowing for the reuse of sections across different blade lengths and types, and the use of flow altering devices to adjust aerodynamic properties to meet target induction factors, simplifying the manufacturing process and reducing production costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional aerodynamic shapes with double curvature contours and multiple airfoil shapes are used, then aerodynamic performance is improved, but device complexity and manufacturing complexity increase
Solution Approach 1:
The blade is divided into multiple longitudinal segments along the spanwise direction, with each segment having a constant cross-sectional shape. This segmentation allows complex aerodynamic performance to be achieved through simple, repetitive geometric units, reducing manufacturing complexity while maintaining aerodynamic effectiveness.
Solution Approach 2:
The invention changes the geometric parameters of the blade by using constant cross-sectional shapes repeated along the span, rather than continuously varying complex contours. This parameter approach simplifies the blade geometry while achieving target aerodynamic performance through optimized segment arrangement and airfoil selection.
2Reliability
If complex aerodynamic shapes are designed, then aerodynamic performance is improved, but manufacturing time and production costs increase
Solution Approach 1:
By segmenting the blade into standardized sections with constant cross-sections, the manufacturing process is simplified and accelerated. Each segment can be manufactured using the same molds and processes, enabling parallel production and reducing overall manufacturing time while maintaining aerodynamic performance.
Solution Approach 2:
The invention uses repeated copying of the same cross-sectional shape along the blade span. This allows standardization of manufacturing molds and processes, significantly reducing production time and costs compared to creating unique complex shapes for each blade section, while achieving target aerodynamic characteristics through proper segment selection and arrangement.
3Reliability
If new blade types are developed with complex designs, then aerodynamic performance is improved, but development time and costs increase
Solution Approach 1:
The segmented design with constant cross-sections allows for modular development and testing. Individual segments can be optimized and validated independently, then assembled into complete blade designs, significantly reducing development time compared to testing entire complex blade designs at once, while achieving target aerodynamic performance.
Solution Approach 2:
The constant cross-sectional segments can be used across multiple blade types and applications, creating a universal design element. This universality reduces development time for new blade types, as the same proven segments can be reused and reconfigured for different aerodynamic requirements, rather than designing entirely new complex shapes for each application.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enables faster development and production of wind turbine blades by simplifying the design and manufacturing process, reducing costs, and allowing for the reuse of existing blade sections, while maintaining near-optimum aerodynamic performance.
Implementation Method 1
a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow
Implementation Method 2
the first longitudinal segment being provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target induction factor at the design point
Data Source
Figure 1
Figure 2
Figure 3~5
AI summary
A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft is described. The rotor comprises a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow, the profiled contour in the radial direction being divided into a root region with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and preferably a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, wherein the airfoil region comprises at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region, the first longitudinal segment comprising a first base part having a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The first base part has an inner dimension that varies linearly in the radial direction of the blade in such a way that an induction factor of the first base part without flow altering devices at a rotor design point deviates from a target induction factor. The first longitudinal segment is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target induction factor at the design point.