Aircraft Wing Micro-Perforations for Boundary Layer Suction and Ice Protection
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Solution Overview
Problem
Existing aircraft boundary layer suction and ice protection systems have complex structures that complicate integration into the wing's upstream portion, necessitating a simplified solution that combines both functionalities effectively.
Innovation Solution
A system featuring a wing with micro-perforations, a perforated tube along the leading edge, a check valve for air intake and backflow prevention, and means for both suction of the boundary layer and blowing hot air for ice protection, where hot air is evacuated directly through the perforations, eliminating the need for a recovery circuit and reducing structural requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a separate recovery circuit is used for ice protection air, then ice protection effectiveness is improved, but device complexity increases
Solution Approach 1:
The patent merges the ice protection air evacuation function with the existing boundary layer suction system. The same suction channels and suction means are used to evacuate both boundary layer air and hot ice protection air through common evacuation openings, eliminating the need for a separate recovery circuit while maintaining ice protection effectiveness
Solution Approach 2:
The suction system is designed to perform multiple functions: it serves as both the boundary layer suction system during cruising flight and the ice protection air evacuation system during take-off and landing phases. The suction channels and evacuation openings are used universally for both purposes, simplifying the overall system structure
2Reliability
If oversized structural elements are used to withstand high pressure, then ice protection reliability is improved, but weight increases
Solution Approach 1:
The patent changes the pressure parameter characteristics by using suction to evacuate hot air rather than relying on high pressure buildup. The suction means create negative pressure to draw out hot air, which eliminates the need for oversized structural elements designed to withstand high positive pressure, thereby reducing wing structure weight while maintaining ice protection reliability
3Reliability
If separate systems are used for boundary layer suction and ice protection, then functional reliability is improved, but device complexity increases
Solution Approach 1:
The patent combines the boundary layer suction system and ice protection system into a single integrated system. The same suction channels, evacuation openings, and suction means are used for both boundary layer suction during cruising flight and hot air evacuation during take-off and landing, simplifying integration into the wing structure while maintaining functional reliability through phase-specific activation
Solution Approach 2:
The system is designed to be dynamic, switching between different operational modes based on flight phase. During cruising flight, the system operates as a boundary layer suction system; during take-off and landing, it switches to ice protection mode. This dynamic adaptability allows a single system to perform multiple functions reliably without requiring separate dedicated systems
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
The system simplifies integration and operation by allowing direct evacuation of hot air, reducing the need for oversized structural elements and facilitating efficient boundary layer suction and ice protection without overpressurization risks.
Implementation Method 1
a check valve (24) coupled to the tube to allow the intake of air into the tube through the flapper valve and to prohibit the backflow of air coming from the tube through the flapper valve
Implementation Method 2
means for sucking the air from this tube in order to suck the boundary layer successively via the micro-perforations of the wall and the perforations of the tube
Implementation Method 3
means for blowing hot air into this perforated tube during the ice protection phase, this hot air being evacuated successively via the perforations of the tube and the micro-perforations of the wall
Data Source
AI summary
A system for suction of the boundary layer of a wing and protection against icing of this wing includes a wall including micro-perforations and delimiting a leading edge extended by a pressure-side wall and by a suction-side wall. The system also includes a perforated tube running along the leading edge, an exhaust duction for sucking air from this tube in order to suck the boundary layer successively via the micro-perforations of the wall and via the perforations of the tube, and a supply duct for blowing hot air into this perforated tube during a phase of protection against icing, this hot air being discharged successively via the perforations of the tube and via the micro-perforations of the wall.