Aircraft Inlet Lip De-Icing at Splice Plates for Uniform Heating
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Solution Overview
Problem
Existing aircraft air inlets with de-icing systems face non-homogeneous temperature distribution due to splice plates, leading to suboptimal de-icing performance on the lip surface.
Innovation Solution
Incorporation of a secondary de-icing system with a heat exchanger and heating body to compensate for the thickness variation caused by splice plates, ensuring homogeneous de-icing capacity across the lip surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If splice plates are used to connect panels in the lip, then the structural integrity and assembly flexibility are improved, but the temperature distribution becomes non-homogeneous and de-icing effectiveness deteriorates
Solution Approach 1:
The patent applies local quality by making the splice plate thermally insulating at specific locations where panels connect, while maintaining thermal conductivity in other areas. This localized thermal insulation prevents heat loss at splice plate regions, ensuring homogeneous temperature distribution across the lip surface without compromising the structural benefits of panel assembly
Solution Approach 2:
The splice plate is constructed as a composite structure with thermally insulating portions (such as foam material or air gaps) and thermally conductive portions (such as metallic support structures). This composite design maintains structural integrity while minimizing thermal bridging effects that would cause non-homogeneous temperature distribution
2Strength
If the lip thickness is increased at splice plate regions for structural support, then the mechanical strength is improved, but the de-icing temperature uniformity deteriorates
Solution Approach 1:
The patent implements local quality by providing thermal insulation specifically at the increased thickness regions of splice plates, while maintaining optimal thickness elsewhere. This localized insulation approach compensates for the thermal mass effect of increased thickness, ensuring uniform temperature distribution without compromising structural strength where it is most needed
3Device complexity
If a single main de-icing system is used, then the system complexity is minimized, but the de-icing coverage and effectiveness deteriorate at splice plate regions
Solution Approach 1:
The patent segments the de-icing system into a main de-icing system for general coverage and supplementary heating elements specifically positioned at splice plate regions. This segmentation ensures that areas with poor thermal characteristics receive targeted heating, achieving complete de-icing coverage while maintaining relatively simple overall system architecture
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 secondary de-icing system ensures uniform de-icing performance by maintaining consistent temperature distribution, enhancing the de-icing effectiveness of the air inlet lip.
Implementation Method 1
a heat exchanger (64) connected to said heating body and configured to transmit said thermal energy towards first and second regions covered by said splice plate
Implementation Method 2
a heating body (62) configured to convert electrical energy into thermal energy
Data Source
AI summary
An air inlet of an aircraft propulsion assembly, comprising a lip which includes juxtaposed panels connected by at least one splice plate. This air inlet combines a main de-icing system and at least one secondary de-icing system which includes at least a main layer, which is made of a thermally conductive material and comprises a through-opening for each fixing element passing therethrough, the main layer being interposed at least partially between the splice plate and at least one of the first and second panels.