Compressor in Wing Box Plenum for Laminar Flow Control
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Solution Overview
Problem
Existing hybrid laminar flow control systems for aircraft are hindered by size, complexity, weight, and high maintenance costs due to the need for extensive piping and ducting systems, which also complicate sealing and accessibility.
Innovation Solution
An aerodynamic body with a load-bearing supporting structure featuring a hollow chamber as a low-pressure suction plenum, integrated compressor, and a perforated panel skin without pipes or valves, where the compressor is located inside the suction plenum to create negative pressure and suck air through the panel skin's openings, reducing complexity and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional piping systems are used to connect suction openings to the suction system, then the system can effectively maintain laminar boundary layer flow, but the size, complexity, weight and cost of the system increase significantly
Solution Approach 1:
The patent merges the suction openings directly into the hollow structural elements (wing box ribs, spars, or leading edge) of the aircraft wing. The structural elements themselves serve as the suction plenum chambers, eliminating the need for separate piping systems. This integration reduces system complexity while maintaining the ability to extract boundary layer air for laminar flow control.
Solution Approach 2:
The hollow structural elements of the wing box serve dual functions: providing structural support and acting as suction plenum chambers for laminar flow control. By making the structural elements multi-functional, the patent eliminates dedicated piping systems while maintaining suction capability across the wing surface.
2Reliability
If extensive piping systems are used for suction, then air can be effectively removed from the boundary layer, but the weight of the system increases
Solution Approach 1:
The patent combines the suction plenum chambers with the load-bearing structural elements of the wing box. By using the existing hollow structural space for suction purposes, no additional weight is added for separate piping systems. The structural elements themselves become the air removal pathways.
3Stress or pressure
If multiple suction components and dedicated vacuum tight joints are used, then the suction system can maintain low pressure areas, but sealing becomes extremely demanding and maintenance effort increases
Solution Approach 1:
The patent integrates the suction plenum chambers directly into the modular structural elements of the wing box. This integration reduces the number of external connections and joints required, simplifying sealing requirements. The structural elements themselves form the sealed chambers, eliminating the need for numerous dedicated vacuum tight joints between separate components.
4Reliability
If traditional suction systems with multiple components are used, then laminar flow control can be achieved, but the cost and maintenance time increase
Solution Approach 1:
The patent merges the suction system with the primary structural elements of the wing, which are already integral to the aircraft airframe. This integration eliminates the need for separate, easily-damaged piping systems that require frequent maintenance. The structural elements serve dual purposes, reducing overall system complexity and maintenance requirements.
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 eliminates the need for pipes and ducts, simplifies maintenance, and reduces weight and cost, enabling broader application of hybrid laminar flow control while maintaining a laminar boundary layer for improved fuel efficiency and reduced emissions.
Implementation Method 1
the compressor is located inside the hollow chamber respectively inside the low-pressure suction plenum and the inlet of the compressor protrudes into the low-pressure suction plenum and the outlet sticks out of the low-pressure suction plenum into an ambient pressure compartment so that a low-pressure within the low-pressure suction plenum established by the compressor results in air suction through the openings of the perforated panel skin
Implementation Method 2
If a negative pressure is applied to the low-pressure suction plenum, air from the area of the outer surface of the perforated panel skin is sucked into low-pressure suction plenum. This allows the necessary amount of the boundary layer at the outer surface of the perforated panel skin to be extracted.
Implementation Method 3
Hybrid laminar flow control (HLFC) systems have been developed for aircraft in an attempt to stabilize the laminar boundary layer flow and to prevent the transition from a laminar boundary layer flow to a turbulent boundary layer flow as long as possible. A laminar boundary layer flow at the outer flow surfaces of an aircraft can reduce the airframe drag
Data Source
Figure 1
AI summary
The invention relates to an aerodynamic body for flying objects having a hybrid laminar flow control, wherein the aerodynamic body comprises: - a load bearing supporting structure (11) having at least one hollow chamber forming a low-pressure suction plenum (18); - a perforated panel skin (20) arranged on the supporting structure of the aerodynamic body having an outer surface (23), the perforated panel skin has a plurality of openings being in fluid communication with the low-pressure suction plenum; and - at least one compressor (40) having at least one inlet (41) and at least one outlet (42); characterized in that - the compressor is located inside the hollow chamber; and - the inlet of the compressor protrudes into the low-pressure suction plenum and the outlet sticks out of the low-pressure suction plenum into an ambient pressure compartment so that a low-pressure within the low-pressure suction plenum established by the compressor results in air suction through the openings of the perforated panel skin.