Fan Casing Cooler with Thermally Sensitive Shape-Change Fins
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Solution Overview
Problem
Current surface coolers in aircraft engines are statically oversized during off-peak conditions, leading to increased aerodynamic drag and specific fuel consumption, as they are designed for maximum engine load, necessitating a solution to adaptively balance cooling performance with drag reduction.
Innovation Solution
A fan casing cooler with a thermally sensitive portion made of materials like aluminum alloy and aluminum silicon carbide, which changes shape in response to temperature changes, passively positioning itself within the airflow path during peak demand and retracting during off-peak conditions to optimize cooling efficiency and reduce drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the cooler is designed for maximum engine load, then cooling performance is improved, but aerodynamic drag increases during off-peak conditions
Solution Approach 1:
The cooler is designed with movable fins that can dynamically adjust their position and orientation based on thermal conditions. During peak engine load, the fins extend into the airflow path to maximize cooling surface area. During off-peak conditions, the fins retract or align with the airflow to minimize aerodynamic drag, thus resolving the contradiction between cooling performance and drag reduction.
Solution Approach 2:
The cooler utilizes thermally sensitive materials that change their physical properties in response to temperature variations. When the engine operates at maximum load and temperatures rise, the thermally sensitive portions activate to position the cooler into the airflow path. When temperatures drop during off-peak conditions, the materials return to their original state, causing the cooler to retract, thereby adapting cooling parameters to match operational demands.
2Temperature
If the cooler is positioned into the airflow path, then cooling effectiveness is improved, but specific fuel consumption increases
Solution Approach 1:
The cooler employs movable fins with variable geometry that can adjust their configuration based on cooling demand. During peak engine load when maximum cooling is required, the fins are positioned to maximize heat transfer surface area exposed to airflow. During off-peak conditions, the fins are repositioned to minimize their impact on airflow, thereby reducing the energy penalty and specific fuel consumption associated with increased drag.
Solution Approach 2:
The cooler incorporates thermally sensitive materials that automatically adjust the cooler's position and fin geometry in response to temperature changes. When engine temperatures indicate peak load operation, the materials activate to deploy the cooler into the optimal position within the airflow path for maximum cooling effectiveness. When temperatures decrease during off-peak operation, the materials cause the cooler to retract, minimizing aerodynamic interference and reducing specific fuel consumption.
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 enhances cooling effectiveness during peak demand while minimizing aerodynamic drag during off-peak conditions, thereby improving specific fuel consumption and overall engine efficiency.
Implementation Method 1
the body includes at least one thermally sensitive portion configured to passively position at least a portion of the fan casing cooler into the air flowing through the annular fan casing in response to a change in a thermal condition
Implementation Method 2
Heat exchangers can be placed in a turbine jet engine fan case, using bypass air to remove lube oil energy through forced convection
Implementation Method 3
Heat is typically transferred from the oil to air by air-cooled oil coolers, and more particularly, surface air-cooled oil cooler systems
Data Source
AI summary
An apparatus and method for cooling a fluid within a turbine engine. A fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler includes a body to confront the peripheral wall with at least one conduit configured to carry a flow of heated fluid to convectively cool the heated fluid with a flow of air through the flow path.


