Active Grille Shutter Flap Profile for Lower Drag and Lift
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Solution Overview
Problem
Existing grille shutter devices experience reduced aerodynamic performance due to lift generation on fins caused by uneven air flow, leading to increased air resistance and decreased cooling efficiency.
Innovation Solution
The grille shutter device incorporates airfoil-shaped flaps with symmetrical and asymmetrical sections, where the symmetrical airfoil portion's thickness gradually increases and decreases along the chord line, and a planar downstream edge, reducing pressure differences and air resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the fins have chamfered portions with arcuate cross-sections that allow air to flow more easily toward the upper side, then the air flow toward the fin is improved, but a pressure difference occurs between upper and lower sides generating lift that reduces aerodynamic performance
Solution Approach 1:
The invention applies asymmetry by configuring the airfoil-shaped fin with an asymmetrical cross-sectional shape where the upper chamfered portion has a larger radius of curvature than the lower chamfered portion. This intentional asymmetrical design allows air to flow more smoothly over the upper surface while maintaining controlled pressure distribution, resolving the contradiction between improving air flow and preventing harmful lift forces.
Solution Approach 2:
The invention changes the geometric parameters of the fin cross-section by specifying different radii of curvature for the upper and lower chamfered portions. By adjusting these curvature parameters, the air flow characteristics are optimized to reduce pressure difference and minimize lift forces while maintaining effective air flow through the grille shutter device.
2Object-affected harmful factors
If the symmetrical airfoil portion thickness gradually increases from the upstream edge toward the first section and then decreases toward the second section, then aerodynamic performance is enhanced and air resistance is minimized, but manufacturing complexity increases
Solution Approach 1:
The invention applies local quality by dividing the fin into distinct sections (first section and second section) with different thickness characteristics. The thickness gradually increases from the upstream edge to the first section and then decreases toward the second section, creating localized variations in geometric properties that optimize aerodynamic performance while maintaining manufacturability through defined regional characteristics.
3Object-affected harmful factors
If the flaps are designed with both symmetrical and asymmetrical sections, then aerodynamic performance is improved, but device complexity increases
Solution Approach 1:
The invention applies segmentation by dividing the airfoil-shaped fin into distinct functional sections: a symmetrical airfoil portion and an asymmetrical airfoil portion. This segmentation allows each section to perform its specific aerodynamic function while maintaining overall structural integrity and simplifying the design process through modular geometric decomposition.
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 design enhances aerodynamic performance by minimizing air resistance and improving cooling efficiency while facilitating easy flap manufacturing and reducing gaps for improved sealing in the closed position.
Implementation Method 1
Each of the flaps includes a symmetrical airfoil portion that forms a portion of the flap between the upstream edge and the second section. The symmetrical airfoil portion is shaped to be symmetrical with respect to a chord line that connects the upstream edge to the downstream edge.
Data Source
AI summary
A grille shutter device includes a frame body having an inlet and airfoil-shaped flaps. The flaps are configured to open or close the inlet by rotating in forward and reverse directions around respective rotary shafts. A section of each flap between an upstream edge and a downstream edge is referred to as a first section. A section of each flap between the first section and the downstream edge is referred to as a second section. Each flap includes a symmetrical airfoil portion. The symmetrical airfoil portion is shaped to be symmetrical with respect to a chord line. A thickness of the symmetrical airfoil portion in a direction that is orthogonal to a direction in which the chord line extends and a direction in which the rotary shaft extends, gradually increases from the upstream edge toward the first section and gradually decreases from the first section toward the second section.