Aircraft Pylon Oil Cooling and De-icing via Heat Exchange
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Solution Overview
Problem
Current propulsion unit suspension systems face challenges with oil heating, leading to reduced performance and increased drag due to thick nacelles, and icing issues at the leading edges of suspension pylons, requiring effective cooling and de-icing solutions without compromising aircraft performance or increasing air bleeding.
Innovation Solution
A suspension pylon architecture featuring an oil exchange circuit with a feed and return line within a hollow arm, an intermediate shaft driving the oil pump, and cooling compartments to manage oil temperature, reducing nacelle thickness and facilitating de-icing through forced convection cooling and heat exchanger functionality.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the gearbox is positioned in the engine nacelle, then the equipment is accessible and easy to maintain, but the nacelle thickness increases causing increased drag and reduced aircraft performance
Solution Approach 1:
The gearbox is extracted from the engine nacelle and repositioned in the fuselage, removing the source of nacelle thickening. This extraction eliminates the drag penalty while maintaining equipment accessibility through the fuselage access points.
Solution Approach 2:
The pylon structure is given multiple functions: it serves as the suspension support, as the housing for the gearbox, and as a heat exchanger for oil cooling. This multi-functionality consolidates components without increasing overall system volume or drag.
2Temperature
If air is bled from the turbine flows for forced cooling, then the oil temperature is controlled, but the turbine engine performance is reduced
Solution Approach 1:
The pylon acts as an intermediary heat exchanger between the oil circuit and the ambient air. Instead of using engine air flows for cooling, the pylon's external surface dissipates heat to the surrounding air, eliminating the need to bleed performance-critical air from the turbine flows.
Solution Approach 2:
The moving pylon itself serves as the cooling surface, utilizing its own structure and motion through the air to provide cooling. The pylon's external surface area is used as a radiator, converting the system's motion into a cooling mechanism without requiring additional energy extraction from the engine.
3Ease of manufacture
If the pylon structure is simplified for cost reduction, then manufacturing cost decreases, but the ability to cool oil and prevent icing is compromised
Solution Approach 1:
The pylon is designed to simultaneously perform structural support, oil cooling, and anti-icing functions through its basic structure. By making the pylon itself the heat exchanger rather than adding separate cooling components, the solution reduces overall system complexity and manufacturing cost while maintaining all required functions.
Solution Approach 2:
The cooling and anti-icing functions are merged into the pylon's structural design. The same surface that provides structural support also serves as the heat exchange surface, eliminating the need for separate cooling systems and reducing manufacturing 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
This solution effectively cools the oil without reducing engine performance, reduces nacelle volume, and addresses icing issues by utilizing the pylon as a heat exchanger, eliminating the need for dedicated de-icing systems and minimizing air bleeding, thus enhancing overall aircraft efficiency and reducing costs.
Implementation Method 1
Solutions involving forced cooling, with air bled from one of the flows, make it possible to hold the temperature
Implementation Method 2
the arm has a structure adapted for cooling the oil exchange circuit at the arm
Implementation Method 3
an intermediate shaft which extends in said arm, said shaft being configured, on the one hand, to be driven by the propulsion unit the arm whereof provides for suspension and, on the other hand, to drive the oil pump in the fuselage
Implementation Method 4
facilitating de-icing through forced convection cooling and heat exchanger functionality
Data Source
AI summary
The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2), wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).