Perforated Heating Layer for Aircraft Ice Protection
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Solution Overview
Problem
Existing ice protection systems for aircraft engines are heavy, inefficient, and require high-temperature materials, which can reduce engine performance and increase weight and drag.
Innovation Solution
A lightweight ice protection system that integrates a heating layer with perforations extending from one surface to the opposite surface, providing both electrically resistive heating and acoustic attenuation, which overlays at least a portion of the acoustic treatment in the nacelle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional bleed air systems are used for ice protection, then ice protection is provided, but engine efficiency is reduced and weight increases
Solution Approach 1:
The patent replaces the mechanical bleed air system with an electrical heating system integrated into the composite nacelle structure. The heating elements are embedded within the composite plies, converting thermal energy delivery from a mechanical fluid-based system to an electrical system, thereby improving engine efficiency while maintaining ice protection capability
Solution Approach 2:
The heating system is merged with the composite nacelle structure itself, rather than being a separate component. The heating elements are embedded within the composite plies during manufacturing, combining the structural function of the nacelle with the ice protection function, thereby reducing overall weight and eliminating the need for separate heating systems
2Use of energy by moving object
If insulated wires are embedded through the laminate structure for power distribution, then electrical current can be delivered, but structural properties are degraded and weight increases
Solution Approach 1:
Instead of routing wires through the thickness of the laminate (z-dimension), the patent distributes heating elements within the plane of the composite plies (x-y dimensions). The heating elements are embedded between plies or within specific plies, changing the dimensional approach from through-thickness penetration to in-plane integration, thereby preserving structural integrity while enabling power distribution
Solution Approach 2:
The patent applies heating elements only where ice protection is needed, rather than using through-thickness wires that would require routing through the entire laminate structure. The heating elements are locally integrated within specific composite plies at the leading edge, providing targeted ice protection while minimizing impact on overall structural properties
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 weight and drag while maintaining noise protection and ice protection, allowing for a shorter nacelle that improves engine efficiency and reduces the need for high-temperature materials.
Implementation Method 1
The heating layer is configured to provide electrically resistive heating to a component
Implementation Method 2
The perforations attenuate aircraft noise. The perforations provide acoustic paths.
Data Source
AI summary
A system and a method include a heating layer including perforations extending from a first surface to a second surface opposite from the first surface. The perforations provide acoustic paths. The heating layer is configured to provide electrically resistive heating to a component. An acoustic layer can be coupled to the heating layer. The perforations extend to the acoustic layer.