Wind Turbine Blade Base Part Segmentation for Axial Induction
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Solution Overview
Problem
The traditional process of designing wind turbine blades is complex and time-consuming, with high production costs due to the need for intricate aerodynamic designs and manufacturing processes, which are not optimized for efficient manufacturing methods.
Innovation Solution
A method that uses a base part with inherent non-ideal aerodynamic design, allowing for modular blade construction by adjusting pitch and rotational speed, and employing flow altering devices to meet target axial induction factors, simplifying the blade design and manufacturing process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional aerodynamic design methods are used to achieve target loading and axial induction, then aerodynamic performance is optimized, but manufacturing complexity and development time increase significantly
Solution Approach 1:
The blade is divided into a base part and separate flow altering devices. The base part has simplified geometry that is easy to manufacture, while the flow altering devices (such as vortex generators or trailing edge flaps) are added separately to achieve the desired aerodynamic performance. This segmentation allows each component to be manufactured independently using simpler processes.
Solution Approach 2:
The base part is designed and manufactured first with simplified geometry. The flow altering devices are then added in a subsequent step to fine-tune the aerodynamic characteristics. This preliminary action approach separates the complex aerodynamic design into manageable stages, reducing overall manufacturing complexity.
2Reliability
If complex aerodynamic shapes with double curvature contours are designed, then target axial induction is achieved, but production costs and development time increase
Solution Approach 1:
The blade design is segmented into a base part with simple geometry and separate flow altering devices. The base part can be manufactured quickly using standard processes, while the flow altering devices are added later to achieve the target axial induction factor, significantly reducing development time.
Solution Approach 2:
Instead of changing the complex geometry of the entire blade, the invention changes specific aerodynamic parameters by adding flow altering devices at strategic locations. These devices modify the flow characteristics to achieve the desired axial induction without requiring time-consuming redesign of the entire blade geometry.
3Reliability
If flow altering devices are added to the blade, then aerodynamic performance is improved, but device complexity increases
Solution Approach 1:
Flow altering devices are added only at specific locations on the blade where they are most effective, rather than modifying the entire blade. This local approach improves aerodynamic performance while minimizing the increase in overall device complexity.
Solution Approach 2:
Instead of redesigning the entire blade geometry, the invention applies partial action by adding flow altering devices only to specific sections of the blade. This achieves the desired aerodynamic performance with minimal additional complexity compared to a complete redesign.
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 reduces development time and production costs by enabling the reuse of base parts for different blade types and lengths, and simplifies the manufacturing process while achieving near-optimum aerodynamic performance.
Implementation Method 1
the profiled contour generating a lift when being impacted by an incident airflow
Data Source
Figure 1
Figure 2
Figure 3~5
AI summary
A method of operating a wind turbine including a rotor comprising a wind turbine blade and having a substantially horizontal rotor shaft is described. The rotor compres 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 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 airfoil region further being divided into at least a first longitudinal segment and a second longitudinal segment, the first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region. The first base part has an inherent non-ideal aerodynamic design so that a substantial longitudinal part of the base part without flow altering devices at a design point deviates from a target axial induction factor, wherein the method comprises the steps of: a) adjusting a pitch of the blade and a rotational speed of the rotor so as to meet the target axial induction factor of the second longitudinal segment, and b) providing and arranging flow altering devices to the first longitudinal segment so as to meet the target axial induction factor of the first longitudinal segment.