Leading Edge Cooling Systems for Hypersonic Airfoils
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Solution Overview
Problem
High-performance aircraft, particularly those with hypersonic capabilities, face challenges in thermal management due to the inefficiency of traditional active cooling systems in tight, wedge-shaped spaces at the leading edge of airfoils, leading to potential stagnation and hot spots.
Innovation Solution
An impingement cooling system that utilizes a fluid dispersal device to project fluctuating streams of coolant onto the internal surface of the leading edge, preventing stagnation by creating turbulence and ensuring continuous coolant circulation, which includes delivery channels generating fluctuating jets and return channels to recycle heated coolant.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional active cooling systems are used in tight wedge-shaped spaces at the leading edge, then cooling capability is provided, but system efficiency deteriorates due to stagnation and hot spots
Solution Approach 1:
The patent applies dynamics by transitioning from static cooling channels to dynamic fluctuating jets. The fluid dispersal device projects fluctuating streams of coolant that dynamically adapt to the concave internal surface geometry, preventing stagnation and improving heat transfer efficiency in the constrained wedge-shaped space.
Solution Approach 2:
The patent implements periodic action through fluctuating jets that oscillate in a periodic manner. This periodic flow pattern ensures continuous coolant circulation across the leading edge surface, preventing thermal stagnation and hot spots while maintaining effective cooling capability.
2Productivity
If aerodynamically sharp airfoils are designed for hypersonic flight, then aerodynamic performance is improved, but thermal management becomes more difficult due to constrained space
Solution Approach 1:
The patent applies local quality by tailoring the cooling system specifically to the concave internal surface geometry of the leading edge. The fluid dispersal device is configured to project fluctuating jets that locally address the thermal challenges of the constrained wedge-shaped space, enabling sharp airfoil designs while maintaining effective thermal management.
Solution Approach 2:
The patent utilizes hydraulics by employing fluid-based cooling through fluctuating jets projected onto the internal surface. This hydraulic approach allows effective heat transfer in the constrained geometry of aerodynamically sharp airfoils, resolving the conflict between aerodynamic performance and thermal management.
3Temperature
If conventional cooling methods are used, then thermal protection is provided, but material selection and design flexibility are constrained by expensive materials and complex systems
Solution Approach 1:
The patent implements self-service through a passive cooling system that utilizes the natural convection and fluctuating jet dynamics to achieve effective cooling. The system self-regulates coolant distribution based on the concave surface geometry, eliminating the need for expensive active cooling components and complex control systems while maintaining thermal protection.
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 solution effectively manages heat transfer in constrained geometries, preventing hot spots and vapor lock, allowing for the use of less expensive materials and reducing thermal constraints on airfoil design while maintaining aerodynamic performance.
Implementation Method 1
projecting a fluctuating stream of fluid from the fluid dispersal device toward an internal surface of the leading edge
Implementation Method 2
channeling fluid from a fluid source to a fluid dispersal device inside the wing
Implementation Method 3
channeling fluid from a fluid source to a fluid dispersal device inside the wing... projecting a fluctuating stream of fluid... toward an internal surface of the leading edge
Implementation Method 4
a first return channel, configured to return coolant from the leading edge to the coolant source
Data Source
AI summary
An impingement cooling system is disclosed, including an airfoil having an aerodynamically sharp leading edge, a fluid source, and a fluid dispersal device connected to the fluid source. The leading edge has a concave internal surface and the fluid dispersal device is configured to project a fluctuating stream of fluid toward the internal surface.