Aircraft Hydrogen Distribution With Near-Engine Compression
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Solution Overview
Problem
Aircraft hydrogen distribution systems face challenges such as overpressure risks due to liquid leaks, complex thermal and pressure requirements, and high insulation needs, especially during idle phases, along with the complexity of high-pressure gaseous distribution and the need for additional pumps and heavy pipes.
Innovation Solution
A hydrogen distribution system using a compressor located near the engine to increase GH2 pressure, simplifying conditioning near the tank and reducing pipe mass and insulation needs, while maintaining low-pressure gaseous distribution and utilizing a saturated tank with a thermodynamically stabilized state to minimize sloshing effects.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If liquid hydrogen is distributed through the aircraft, then hydrogen can be stored in a compact form, but overpressure risks occur due to liquid leaks and heat ingress
Solution Approach 1:
The system changes the physical state parameter of hydrogen from liquid to gaseous form for distribution. The liquid hydrogen is vaporized in a controlled manner through heating elements, converting it to gaseous hydrogen that can be safely distributed at lower pressures, thereby eliminating overpressure risks associated with liquid leaks while maintaining storage density through the liquid phase in the tank.
Solution Approach 2:
The patent introduces an intermediary vaporization system between the liquid hydrogen tank and the distribution network. This intermediary system includes heating elements and flow control devices that safely convert liquid hydrogen to gaseous hydrogen, acting as a buffer that prevents direct contact between liquid hydrogen and the distribution system, thereby reducing overpressure risks.
2Power
If high-pressure gaseous distribution is used, then hydrogen can be delivered to consumers, but distribution pipe technology becomes complex and heavy
Solution Approach 1:
The system segments the hydrogen distribution function into two distinct zones: a low-pressure gaseous distribution zone for the majority of the aircraft interior, and a localized high-pressure zone only at the engine interface. This segmentation allows the use of lighter, simpler pipes throughout most of the system while maintaining high-pressure capability only where necessary for engine fuel delivery.
Solution Approach 2:
The patent applies different pressure characteristics to different parts of the distribution system. The main distribution network operates at low pressure with simpler, lighter pipes, while only the immediate engine interface requires high-pressure capability. This local quality approach allows the system to maintain high-pressure delivery to consumers without requiring high-pressure infrastructure throughout the entire aircraft.
3Power
If a centrifugal pump is used to maintain NPSP, then hydrogen can be delivered to the engine, but system complexity increases especially during idle and transient phases
Solution Approach 1:
The patent replaces the mechanical centrifugal pump system with a gas-driven compression system. Instead of using a mechanical pump that requires complex control for NPSP maintenance, the system uses the expansion of gaseous hydrogen through a gas turbine or similar gas-driven mechanism to provide the necessary pressure differential, thereby eliminating the mechanical pump and its associated control complexity.
Solution Approach 2:
The system employs self-regulating flow control mechanisms that automatically adjust hydrogen flow based on engine demand without requiring active pump control. The design includes pressure-regulating valves and flow control elements that self-adjust to maintain proper delivery conditions, eliminating the need for complex pump control systems especially during idle and transient operations.
4Stability of the object's composition
If insulation is increased to maintain liquid hydrogen, then hydrogen remains in liquid form, but system mass and thermal management complexity increase
Solution Approach 1:
The system changes the temperature parameter of hydrogen from cryogenic liquid temperatures to warmer gaseous temperatures for distribution. By vaporizing the liquid hydrogen and maintaining it in a gaseous state at higher temperatures, the system eliminates the need for heavy cryogenic insulation, thereby reducing overall system mass while maintaining hydrogen stability through controlled vaporization and flow management.
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
Reduces leakage risks, simplifies engine interface testing, and minimizes maintenance by using a simplified conditioning system with reduced pipe mass and insulation, while maintaining high-pressure hydrogen delivery to consumers.
Implementation Method 1
a compressor downstream of the conditioning system and configured to receive the gaseous hydrogen stream and provide a high-pressure gaseous hydrogen stream
Implementation Method 2
a heater downstream of the compressor and configured to receive the high-pressure gaseous hydrogen stream and provide a high-temperature, high-pressure gaseous hydrogen stream
Implementation Method 3
Hydrogen (H2) is stored as liquid hydrogen (LH2) in a cryogenic tank at a temperature of approximately −253° C. (roughly 20 Kelvin (K))
Implementation Method 4
a conditioning system configured to provide a gaseous hydrogen stream downstream from the tank towards the hydrogen consumer
Data Source
AI summary
A hydrogen distribution system for supplying hydrogen to a hydrogen consumer comprising: a tank storing a liquid hydrogen fuel; a conditioning system configured to provide a gaseous hydrogen stream downstream from the tank towards the hydrogen consumer; a compressor downstream of the conditioning system and configured to receive the gaseous hydrogen stream and provide a high-pressure gaseous hydrogen stream; a heater downstream of the compressor and configured to receive the high-pressure gaseous hydrogen stream and provide a high-temperature, high-pressure gaseous hydrogen stream; and, a valve downstream of the heater and configured to adjust a flow of the high-temperature, high-pressure gaseous hydrogen stream; wherein the hydrogen consumer is downstream of the valve and configured to receive the high-temperature, high-pressure gaseous hydrogen stream and provide energy by consuming hydrogen from the high-temperature, high-pressure gaseous hydrogen stream. Also, an aircraft with such a system.