Capillary-Integrated Composite De-Icing for Gas Turbine Engines
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Solution Overview
Problem
Gas turbine engines face challenges in preventing ice accumulation on composite materials due to low transverse thermal conductivity, leading to inefficiencies in de-icing and potential engine flameouts during icing conditions.
Innovation Solution
The integration of capillaries adjacent to the external surfaces of turbine engine components, secured by a composite layer, allows for efficient heat transfer and ice prevention using heated airflow, addressing the low thermal conductivity issue.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If heated air is channeled through composite components to de-ice them, then ice accumulation is reduced, but the low transverse thermal conductivity of composite material requires relatively hot air which penalizes overall engine efficiency
Solution Approach 1:
The patent introduces capillaries as intermediary elements that are positioned adjacent to the external surface of composite components. These capillaries serve as thermal conduits that transfer heat from heated air to the component surface more efficiently than direct channeling through the composite material, thereby reducing the temperature requirement of the heated air and improving engine efficiency while maintaining effective ice prevention
Solution Approach 2:
The patent segments the thermal transfer function by separating the heated air source from the component surface that needs de-icing. Instead of requiring heat to traverse the entire composite thickness, the system uses capillaries to deliver heat directly to the external surface, creating a segmented thermal path that overcomes the low transverse thermal conductivity of the composite material
2Weight of moving object
If composite materials are used for engine components, then weight is reduced, but transverse thermal conductivity is low making de-icing difficult
Solution Approach 1:
The patent creates a hybrid composite structure by integrating capillaries into or onto the composite component. This new composite system combines the lightweight advantage of composite materials with the high thermal conductivity of the capillary material, achieving both low weight and effective heat transfer for de-icing applications
Solution Approach 2:
The patent applies local quality enhancement by concentrating thermal conductivity improvements specifically at the surface regions where ice prevention is needed. The capillaries are positioned adjacent to the external surface, providing localized high thermal conductivity zones without requiring the entire composite component to have high thermal conductivity, thus maintaining the overall lightweight composite structure
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 reduces ice formation on gas turbine engine components, enhances engine efficiency, and prevents compressor stall margin issues and flameouts by directing heated air directly to the surface, using less compressor bleed air and potentially lower temperature resins.
Implementation Method 1
allows for efficient heat transfer and ice prevention using heated airflow
Data Source
AI summary
A method for manufacturing a turbine engine component includes forming a component to include a first side and an opposite second side, positioning at least one capillary adjacent to an external surface of at least one of the first and second sides, and securing the at least one capillary to the component with at least one composite layer.