Fuel Cell Turbocompressor Propulsion for Altitude-Responsive Thrust
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Solution Overview
Problem
Aircraft propulsion systems face challenges in delivering varying thrust levels during different flight stages due to pressure differences, with gas turbines being the preferred but inefficient option, and hydrogen fuel cells struggling to meet the power demands without significant economic drawbacks.
Innovation Solution
A fuel cell propulsion system with a compressor and turbine arrangement that adjusts to altitude changes, using ambient air or ECS exhaust, and incorporating oxygen enrichment to optimize power delivery.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If gas turbine engines are used for aircraft propulsion, then high specific power and thrust delivery are achieved, but environmental demands and inefficiency worsen
Solution Approach 1:
The patent combines a fuel cell stack with a turbine-compressor system to merge the advantages of electrochemical energy conversion with mechanical thrust generation. The fuel cell provides electrical power while the turbine-compressor recovers exhaust energy, creating a hybrid system that achieves both high specific power and improved efficiency
Solution Approach 2:
The patent introduces an intermediary turbine-compressor system that bridges the fuel cell output and the aircraft propulsion requirement. The turbine recovers energy from the fuel cell exhaust gases and drives the compressor, which pressurizes air for the fuel cell, creating an efficient energy cycle
2Object-affected harmful factors
If hydrogen fuel cell systems are used for aircraft propulsion, then environmental friendliness is improved, but specific power and thrust delivery worsen
Solution Approach 1:
The patent employs a dynamic turbine-compressor system that can adjust its operation based on flight conditions and altitude. The variable geometry turbine and compressor allow the system to optimize power delivery across different flight regimes, achieving high specific power when needed while maintaining environmental benefits
Solution Approach 2:
The patent changes the operational parameters of the fuel cell system by using the turbine to recover exhaust energy and drive the compressor, which increases the efficiency and power output of the fuel cell stack, thereby improving specific power while maintaining environmental friendliness
3Quantity of substance
If fuel cell systems consume hydrogen with ambient air, then oxygen availability is improved, but parasitic losses from compression worsen
Solution Approach 1:
The patent implements a self-service system where the fuel cell exhaust gases themselves drive the turbine-compressor that supplies air to the fuel cell. The waste heat and kinetic energy in the exhaust are recovered to power the compression system, eliminating the need for separate parasitic compression systems and reducing overall energy losses
4Quantity of substance
If two stage compression is used for high altitude operation, then oxygen delivery is improved, but system complexity and efficiency at low altitude worsen
Solution Approach 1:
The patent uses a dynamic turbine-compressor system with variable geometry that can adjust its compression ratio and flow characteristics based on altitude and power demand. This single dynamic system replaces the need for fixed two-stage compression, reducing complexity while maintaining oxygen delivery capability across all altitudes
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 system provides efficient and economical flight by tailoring propulsive output to flight conditions, reducing parasitic losses, and minimizing oxygen waste, thus enhancing energy efficiency and reducing system weight.
Implementation Method 1
a fuel cell arrangement comprising at least one fuel cell
Implementation Method 2
a compressor arrangement comprising a first compressor in fluid communication with the air source and a fuel cell of the fuel cell arrangement
Implementation Method 3
a turbine arrangement comprising a first turbine mechanically coupled to the first compressor, wherein the first turbine is in fluid communication with the at least one fuel cell
Data Source
AI summary
The present invention relates to an aircraft propulsion system (100) comprising: a fuel cell arrangement comprising at least one fuel cell (110); an air source (130) for providing air to the fuel cell arrangement; a compressor arrangement comprising a first compressor (120) in fluid communication with the air source and a fuel cell of the fuel cell arrangement; and, a turbine arrangement comprising a first turbine (124) mechanically coupled to the first compressor, wherein the first turbine is in fluid communication with the at least one fuel cell (110), the system being arranged so that, in use, air from the air source (130) flows in turn to the first compressor (120), the fuel cell arrangement and the first turbine (124).