Aircraft Power Source Using Solid Oxide and Proton Exchange Membrane Fuel Cells
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Solution Overview
Problem
Conventional aircraft power systems rely heavily on jet turbine engines and Auxiliary Power Units (APUs), which are inefficient and environmentally polluting, and lack redundancy for electrical, hydraulic, and pneumatic power generation.
Innovation Solution
Integration of solid oxide fuel cells (SOFCs) and proton exchange membrane fuel cells (PEMFCs) with power converters and batteries to create a separate, efficient, and redundant power source for aircraft, capable of supplying electricity, hydraulics, and compressed air, decoupling propulsion from power generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If jet turbine engines and APU are used to provide electrical, hydraulic, and pneumatic power, then power generation capability is achieved, but system efficiency is reduced and environmental pollution increases
Solution Approach 1:
The power generation system is segmented into independent fuel cell modules (SOFC and PEMFC) that operate separately from the jet turbine engines. This allows the engines to focus solely on propulsion while fuel cells handle electrical, hydraulic, and pneumatic power generation, improving overall system efficiency and reducing emissions associated with using engines for dual purposes
Solution Approach 2:
The patent replaces conventional mechanical power generation systems (jet turbine engines and APU) with electrochemical fuel cell systems. This substitution eliminates the need to burn fuel mechanically to generate power, instead using electrochemical reactions to produce electricity directly, thereby reducing energy loss and environmental pollution
2Reliability
If jet turbine engines provide all power outputs (electrical, hydraulic, pneumatic), then power generation capability is maintained, but redundancy is lacking
Solution Approach 1:
The power system is divided into multiple independent power sources: jet turbine engines for propulsion, SOFC for electrical/hydraulic/pneumatic power, PEMFC for electrical power, and batteries for supplemental electrical power. This segmentation creates redundancy where each system can compensate for failures in others, while maintaining manageable complexity through functional specialization
Solution Approach 2:
The patent changes the operational parameters of the aircraft power system by introducing multiple power sources with different operational characteristics. The fuel cells operate at different temperatures and power levels, allowing the system to adapt to various flight conditions and failure scenarios, thereby improving reliability without excessive complexity
3Productivity
If turbine engine is used for both propulsion and power generation, then all power needs are met, but propulsion efficiency is reduced
Solution Approach 1:
The patent extracts the power generation function from the jet turbine engine by introducing separate fuel cell systems (SOFC and PEMFC) dedicated to producing electrical, hydraulic, and pneumatic power. This allows the turbine engine to be optimized exclusively for propulsion, improving propulsion efficiency while the extracted power generation function is handled by the fuel cells
Solution Approach 2:
The fuel cell systems are designed to provide multiple functions: SOFC generates electrical, hydraulic, and pneumatic power; PEMFC generates electrical power; batteries provide supplemental electrical power. This multi-functionality replaces the single-engine dual-purpose system, allowing the turbine to focus on propulsion while fuel cells handle all power generation needs
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 enhances aircraft power efficiency, reduces emissions, improves availability, and reduces maintenance needs by allowing the turbine engine to focus solely on propulsion, while providing a cleaner and more reliable power system.
Implementation Method 1
A proton exchange membrane fuel cell (PEMFC) and a solid oxide fuel cell (SOFC) provide direct current (DC) electrical power from a chemical process
Implementation Method 2
A proton exchange membrane fuel cell (PEMFC) and a solid oxide fuel cell (SOFC) provide direct current (DC) electrical power from a chemical process
Implementation Method 3
at least one battery electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and the aircraft distribution network to supply electricity to the aircraft and to be recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell
Data Source
AI summary
A power source for an aircraft including a solid oxide fuel cell and a proton exchange membrane fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell.