Fuel Cell Compressor Motor Windings for Aircraft Propulsion Redundancy
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Solution Overview
Problem
Aircraft with electrical propulsion systems that rely on multiple sets of fuel cells for redundancy face significant mass and spatial challenges due to the need for multiple compressors, and a single compressor fault can lead to a failure of all connected fuel cells, compromising system availability.
Innovation Solution
Implementing a single compressor connected to multiple sets of fuel cells, with the electric motor driving the compressor having multiple electrical windings supplied by distinct fuel cell sets, allowing continued operation with reduced power in case of faults, and using redundant cooling systems with similarly configured windings for each set of fuel cells.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of stationary object
If a single compressor is used to supply multiple sets of fuel cells, then the mass and spatial requirements are reduced, but the system reliability deteriorates because a fault in the electric motor or controller would cause all connected fuel cells to fail
Solution Approach 1:
The electric motor is divided into multiple independent electrical windings, where each winding can be supplied by a different set of fuel cells. This segmentation allows the motor to continue operating with reduced power if one winding or its supply fails, preventing total system failure and maintaining propulsion availability.
2Reliability
If multiple compressors are associated with each set of fuel cells, then the system reliability is improved, but the mass and spatial requirements increase significantly
Solution Approach 1:
Multiple fuel cell sets share a common compressor resource. The compressor is supplied by multiple electrical windings from different fuel cell sets, allowing the single compressor to serve multiple fuel cell sets simultaneously. This merging reduces the total number of compressors needed while maintaining system reliability through redundant electrical supply paths.
Solution Approach 2:
The single compressor performs multiple functions by supplying compressed air to multiple different sets of fuel cells. The electric motor driving the compressor can draw power from any of the connected fuel cell sets, making the compressor a universal component that serves the entire propulsion system rather than being dedicated to a single fuel cell set.
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 configuration reduces the number of compressors and associated mass and space requirements while ensuring the propulsion system's availability by allowing continued operation with reduced power in case of faults, maintaining system functionality even with faulty components.
Implementation Method 1
The fuel cells convert into electricity chemical energy resulting from a reaction of hydrogen in the presence of oxygen
Implementation Method 2
A compressor compresses ambient air and the compressed air is supplied to the input(s) to the sets of fuel cells to supply oxygen to the set of fuel cells
Data Source
AI summary
The electrical supply system (10) of an electrical propulsion system (4) of an aircraft (1) includes: two first sets of fuel cells (FC11, FC12), configured to supply electrically an electric motor driving a propulsion propeller; a first compressor (C1) configured to supply compressed air to at least part of the at least two first sets of fuel cells (FC11, FC12); and a first electric motor (M1) designed to drive the first compressor. The first electric motor (M1) includes electrical windings (W1a, W1b), each electrical winding supplied electrically by a set of distinct fuel cells from amongst the at least two first sets of fuel cells (FC11, FC12).