Composite Aerospace Component Thermal Insulation
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Solution Overview
Problem
Composite aerospace components used in gas turbine engines experience significant strength reduction when exposed to elevated temperatures during a fire event, increasing the risk of failure under mechanical load.
Innovation Solution
A structurally-integrated aerospace component comprising a metallic layer, a composite layer with reinforcing fibers in a matrix material, and an insulating layer with lower thermal conductivity than the composite layer, where the metallic layers can be perforated or meshed and made from materials like copper, nickel-based alloys, or ferrous alloys, and the reinforcing fibers are carbon or glass fibers in a polymer matrix.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If a composite aerospace component is used to reduce weight, then weight is reduced, but strength is significantly reduced when exposed to elevated temperatures
Solution Approach 1:
The patent applies composite materials by combining a metallic layer with a composite layer containing reinforcing fibers embedded in a matrix material. This creates a hybrid structure that leverages the high-temperature strength of metals and the lightweight properties of composites, resolving the contradiction between weight reduction and maintaining strength at elevated temperatures.
Solution Approach 2:
The patent introduces an insulating layer as an intermediary between the metallic layer and the composite layer. This insulating layer has lower thermal conductivity than the composite layer, serving as a thermal barrier that protects the composite layer from heat exposure, thereby maintaining structural strength while keeping the component lightweight.
2Strength
If an insulating layer with lower thermal conductivity is added between the metallic layer and composite layer, then temperature rise is delayed and structural strength is maintained, but device complexity increases
Solution Approach 1:
The insulating layer serves multiple functions: it acts as a thermal barrier to delay temperature rise, provides structural support as part of the layered construction, and interfaces between the metallic and composite layers. By combining multiple functions in a single layer, the patent reduces the need for additional separate components, thereby limiting the increase in device complexity.
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 solution effectively delays temperature rise and maintains structural strength of the composite components during a fire event, preventing rupture and allowing for safe engine shutdown while reducing part weight by efficiently dissipating heat and providing structural support.
Implementation Method 1
an insulating layer having a thermal conductivity that is lower than a thermal conductivity of the composite layer
Implementation Method 2
The solution effectively delays temperature rise and maintains structural strength of the composite components during a fire event, preventing rupture and allowing for safe engine shutdown while reducing part weight by efficiently dissipating heat
Data Source
AI summary
An aerospace component, for example, used in a gas turbine engine, includes the following structurally-integrated layers: a metallic layer and a composite layer having reinforcing fibers embedded in a matrix material. The aerospace component can also include an insulating layer disposed between the metallic layer and the composite layer where the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer.