Aero Engine Surface Cooler Airfoil Flow Guide
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Solution Overview
Problem
Existing air and oil coolers in gas turbine engines face significant pressure losses due to protruding fins or components within the bypass duct, which reduces their heat transfer performance while increasing fuel burn.
Innovation Solution
A surface cooler design featuring an airfoil shaped flow guide member and radially projecting heat transfer members within an annular bypass duct, where the cooler member is directly connected to the flow guide member and supported by these members on the duct walls, minimizing pressure loss while maintaining heat transfer efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If protruding fins or components are added to increase contact area, then heat transfer performance is improved, but pressure loss increases
Solution Approach 1:
The flow guide member is shaped with a curved outer surface resembling an airfoil cross-section, which streamlines the bypass air flow and reduces turbulence and pressure losses compared to flat or angular configurations
Solution Approach 2:
The invention transitions from traditional flat plate fin configurations to a three-dimensional airfoil-shaped flow guide member that utilizes the radial dimension within the bypass duct, allowing the cooling surface to extend radially outward while maintaining streamlined flow characteristics
2Temperature
If cooler components are disposed within the bypass duct, then cooling efficiency is improved, but fuel consumption increases
Solution Approach 1:
The airfoil-shaped flow guide member reduces flow separation and turbulence in the bypass duct, minimizing the energy penalty associated with the cooler's presence and thereby reducing fuel consumption
Solution Approach 2:
The invention optimizes the geometric parameters of the flow guide member, including the curvature radius of the outer surface and the radial extension distance, to achieve the best balance between heat transfer performance and pressure loss, ultimately reducing 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
The design reduces total pressure loss and enhances heat transfer performance, leading to improved cooler efficiency and reduced fuel consumption in gas turbine engines.
Implementation Method 1
an airfoil shaped flow guide member including a leading edge and a trailing edge with respect to an air stream passing axially through the annular bypass duct
Implementation Method 2
a plurality of heat transfer members spaced apart one from another and radially projecting from the cooler member
Implementation Method 3
hot fluid flowing through the cooler is cooled by a bypass air stream passing through a bypass section
Data Source
AI summary
A gas turbine engine has a surface cooler having a cooler member defining a fluid passage and at least partially contained in an airfoil shaped flow guide member. The cooler member is disposed within a bypass duct and supported on one of the duct walls. The flow guide member provides a smooth outer surface to guide a main portion of a bypass air stream passing over the surface cooler, and defines an inner air channel between the flow guide member and that supporting one of the duct walls for a secondary portion of the bypass air stream to pass through the inner air channel.