Wingtip Air Inlet System for Drag Reduction
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Solution Overview
Problem
Current aircraft systems face issues with increased drag, fuel consumption, and reduced efficiency due to the use of main engine bleed air for wing anti-icing and environmental control, as well as the need for drag-reducing air inlet systems.
Innovation Solution
An ambient air inlet system positioned in the wingtip fence or winglet, coupled with an air pressurization device, which extracts and compresses air to reduce drag and power wing anti-icing and environmental control systems without relying on main engine bleed air, using electrically powered air compressors and heat transfer ducts for cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If main engine bleed air is used for wing anti-icing and environmental control, then these systems can be powered, but drag increases and fuel consumption rises
Solution Approach 1:
The patent extracts the air supply function from the main engine bleed air system and relocates it to electrically powered air compressors positioned in the wing roots. This separation eliminates the drag penalty associated with engine inlet positioning while maintaining the necessary air supply for anti-icing and environmental control systems.
Solution Approach 2:
The patent replaces the mechanical bleed air extraction system with electrically powered compressors. This substitution allows air to be compressed and supplied to anti-icing and environmental control systems without relying on engine bleed air, thereby reducing drag and fuel consumption while maintaining system reliability.
2Temperature
If precoolers are used to reduce bleed air temperatures, then air temperature is controlled, but pressure drop occurs and aircraft efficiency decreases
Solution Approach 1:
The patent removes the precooling function from the traditional engine bleed air path and relocates it to a separate electrically powered compression and cooling system. This extraction eliminates the pressure drop penalties associated with precoolers while maintaining temperature control through dedicated cooling equipment positioned away from the engine inlet.
Solution Approach 2:
The patent replaces the mechanical precooler system with an electrically powered compression and cooling system. This substitution maintains temperature control capability while avoiding the pressure drop and efficiency penalties inherent in traditional precooler designs.
3Stress or pressure
If air compressors are positioned to extract ram air pressure, then pressure and efficiency advantage is gained, but drag is added to the aircraft
Solution Approach 1:
The patent positions air compressors in the wing roots where local airflow conditions provide sufficient pressure without requiring dedicated inlet structures. This localized positioning exploits the natural pressure distribution around the wing to power anti-icing and environmental control systems without adding drag penalty.
Solution Approach 2:
The patent uses the wing structure itself as an intermediary to deliver pressurized air from the compressors to the anti-icing and environmental control systems. This intermediary approach eliminates the need for separate inlet structures and reduces drag while maintaining pressure delivery capability.
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 effectively reduces drag, eliminates the need for main engine bleed air, and enhances aircraft efficiency by utilizing ambient air for anti-icing and environmental control, eliminating the need for precoolers and reducing fuel burn.
Implementation Method 1
an air pressurization device coupled to the ambient air inlet, wherein the air pressurization device has an inlet oriented toward the ambient air inlet; and wherein the air pressurization device has an outlet oriented toward an interior of the aircraft
Implementation Method 2
a heat transfer anti-icing duct coupled to an outlet of the air compressor; wherein the heat transfer duct is positioned along a leading edge of the wing
Implementation Method 3
an outlet of the air pressurization device is coupled to the heat exchanger; and wherein the pressurized air passes through the heat exchanger
Data Source
AI summary
A system for reducing drag on an aircraft includes an ambient air inlet positioned in or near a wingtip fence and or winglet of the aircraft and an air pressurization device, such as an air compressor, coupled to the ambient air inlet. The air pressurization device has an inlet oriented toward the ambient air inlet. The air pressurization device has an outlet oriented toward an interior of the aircraft.