Aircraft Propeller De-Icing Switch Layout for Passive Cone Heat Dissipation
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Solution Overview
Problem
Existing de-icing systems for aircraft turbine engine propellers suffer from overheating issues due to power electronics components, requiring ventilation devices that increase on-board mass, complexity, and cost, while also failing to efficiently dissipate heat and balance the propeller's weight and aerodynamics.
Innovation Solution
Mounting electrical de-icing switches on the inner face of the propeller's cone to transfer dissipated electrical power by thermal conduction into the cone's wall, eliminating the need for cooling devices and balancing the propeller's weight and aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If power electronics components (switches) are mounted inside the cone to control heating elements, then de-icing control is achieved, but heat dissipation becomes problematic requiring additional ventilation devices
Solution Approach 1:
The patent merges the heat dissipation function with the existing cone structure by mounting the power electronics components directly on the inner face of the cone. The cone's outer surface acts as a heat sink, eliminating the need for separate ventilation devices. This combines the structural support function with the thermal management function in a single integrated solution.
Solution Approach 2:
The cone structure serves dual purposes: it provides structural support for mounting the switches and simultaneously acts as a heat dissipation pathway. The natural thermal conduction through the cone wall and convection from its outer surface provide self-service cooling without requiring additional active ventilation systems.
2Temperature
If ventilation devices are added to cool power electronics, then heat dissipation is improved, but on-board mass increases
Solution Approach 1:
The ventilation function is merged with the cone structure itself. The cone's wall thickness and material properties are utilized as the primary heat dissipation pathway, eliminating the need for separate ventilation components that would add mass to the propeller assembly.
Solution Approach 2:
The cone structure provides passive heat dissipation through its inherent thermal conductivity and surface area exposure to the surrounding environment. This self-service cooling mechanism avoids the need for active ventilation systems that would increase the moving mass of the propeller.
3Reliability
If switches are mounted in the cone cavity, then de-icing control is achieved, but propeller balance and aerodynamics are affected
Solution Approach 1:
The patent acknowledges the asymmetric placement of switches on the cone's inner face and compensates for the resulting imbalance. The mounting positions and distribution of switches are strategically arranged to minimize aerodynamic disruption and maintain propeller balance during rotation.
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
Efficient heat dissipation and de-icing of the propeller's blades and cone without additional cooling devices, reducing on-board mass and complexity, and improving the propeller's balance and aerodynamic performance.
Implementation Method 1
Mounting electrical de-icing switches on the inner face of the propeller's cone to transfer dissipated electrical power by thermal conduction into the cone's wall
Implementation Method 2
The heating elements take the form of heating mats comprising electrical resistors, which are activated in the presence of icing conditions
Data Source
AI summary
The invention relates to a propeller (1) of an aircraft turbine engine, comprising a cone (2) and a plurality of blades (3), the propeller (1) comprising a plurality of electrical de-icing members (4) rigidly connected to a wall (30) of the blades (3), and a control system (6) electrically connected to the electrical de-icing members (4) and comprising at least one electrical switch (7A) having a variable switching duty cycle which is configured, using an input electrical power (Pe), to distribute an output electrical power (Ps) to the electrical de-icing members (4) and to emit a dissipated electrical power (Pd) in the form of heat, at least one electrical switch (7A) of the control system (6) being mounted on an inner face (21) of a wall (20) of the cone (2) so as to transfer the dissipated electrical power (Pd) by thermal conduction into the wall (20) of the cone.The invention relates to a propeller (I) of an aircraft turbine engine, comprising a cone (2) and a plurality of blades (3), the propeller (I) comprising a plurality of electrical de-icing members (4) rigidly connected to a wall (30) of the blades (3), and a control system (6) electrically connected to the electrical de-icing members (4) and comprising at least one electrical switch (7A) having a variable switching duty cycle which is configured, using an input electrical power (Pe), to distribute an output electrical power (Ps) to the electrical de-icing members (4) and to emit a dissipated electrical power (Pd) in the form of heat, at least one electrical switch (7A) of the control system (6) being mounted on an inner face (21) of a wall (20) of the cone (2) so as to transfer the dissipated electrical power (Pd) by thermal conduction into the wall (20) of the cone.