Aircraft Wing Rib With Integrated Suction Conduit
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Solution Overview
Problem
Incorporating hybrid laminar flow control systems into aircraft wings is challenging due to limited space, especially when other systems like high-lift devices and ice protection systems are also required in the same region, and maintaining laminar flow becomes difficult at higher cruise Mach numbers.
Innovation Solution
An aircraft wing rib with an integrated suction conduit that applies negative pressure through a U-shaped open channel and duct system, fluidically coupled to a source of negative pressure, which is integrated into the structural rib section and wing skin, allowing for efficient stabilization of the laminar boundary layer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If an HLFC system is incorporated into a wing, then the laminar boundary layer can be stabilized and drag reduced, but the device complexity and space requirements increase due to limited space within the wing structure
Solution Approach 1:
The suction conduit is integrated directly into the structural rib section, merging the HLFC suction function with the existing structural support element. This eliminates the need for separate suction ducting and reduces overall system complexity while maintaining the energy-saving benefits of laminar flow control
Solution Approach 2:
The rib structure serves dual purposes: providing structural support to the wing and housing the suction conduit for laminar flow control. This multi-functionality reduces the number of separate components needed, thereby reducing device complexity while achieving drag reduction and fuel consumption savings
2Reliability
If an HLFC system is incorporated into a wing, then the laminar boundary layer can be stabilized, but the space occupation increases when other systems like high-lift devices and ice protection systems are also required
Solution Approach 1:
The suction conduit is merged with the structural rib section, utilizing the existing structural space rather than adding separate dedicated space for the HLFC system. This allows the rib to simultaneously provide structural support and house the suction function, minimizing additional space occupation while maintaining reliable laminar boundary layer stabilization
Solution Approach 2:
The suction conduit is nested within the structural rib section, similar to how one object can be placed inside another. This nesting approach allows the HLFC system to occupy space that would otherwise be unused or structural, rather than requiring additional external space, thereby coexisting with other wing systems like high-lift devices and ice protection systems
3Speed
If the cruise Mach number increases beyond Mach 0.70, then the aircraft speed increases, but it becomes increasingly difficult to maintain a laminar boundary layer with wing shape alone
Solution Approach 1:
The system uses pneumatic suction through the suction conduit to actively remove disturbances from the boundary layer. This pneumatic control mechanism enables reliable laminar boundary layer maintenance at higher cruise Mach numbers where passive wing shape design alone becomes insufficient
Solution Approach 2:
The system changes the pressure parameter within the boundary layer by applying suction, creating a negative pressure gradient that stabilizes the laminar flow. This parameter change allows the boundary layer to remain laminar at higher speeds where increased Reynolds number and sweep would normally cause transition to turbulent flow
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 stabilizes the laminar boundary layer, reduces drag, and minimizes space occupation, contributing to lower fuel consumption and emissions while accommodating other systems within the wing's limited space.
Implementation Method 1
a suction conduit to which, in use, a pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. The pressure may be referred to as a negative pressure since it is less than the pressure at the outer surface of the wing skin
Implementation Method 2
The pressure may also be referred to as a reduced pressure, a low pressure, or a suction pressure (i.e. it causes suction at the outer surface of the wing skin)
Data Source
AI summary
There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib.