Aircraft Hydrogen Heating Layout to Cut Cryogenic Conduit Weight
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Solution Overview
Problem
The use of complex double-walled pipes for channeling cryogenic hydrogen in hydrogen-powered aircraft results in high costs and substantial weight increase due to the significant distance between the high-pressure pump and the heat exchanger, necessitating numerous fittings.
Innovation Solution
Positioning the hydrogen heating system in the fuselage near the pump, within 5 meters of the fuel tank, and using a combination of heat exchangers and conduits to efficiently heat hydrogen from a liquid to a gaseous state, reducing the length of double-walled conduits and simplifying the system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the heat exchanger is positioned far from the fuel tank in hydrogen-powered aircraft, then the turbomachine can be located optimally for propulsion, but the conduit length increases substantially causing weight increase and higher costs
Solution Approach 1:
The patent divides the hydrogen supply system into distinct functional segments: a first conduit connecting the fuel tank to the pump, a second conduit connecting the pump to the heat exchanger, and a third conduit connecting the heat exchanger to the turbomachine. This segmentation allows each component to be optimally positioned independently, reducing the overall conduit length and weight while maintaining propulsion efficiency.
Solution Approach 2:
The pump serves as an intermediary component positioned between the fuel tank and the heat exchanger. By placing the pump near the fuel tank and using it as a connection point, the system reduces the distance the hydrogen must travel through insulated conduits, thereby reducing conduit weight and cost while still delivering hydrogen to the turbomachine.
2Reliability
If complex double-walled pipes are used to channel cryogenic hydrogen over long distances, then hydrogen can be delivered to the turbomachine, but the number of fittings increases causing cost increase and weight increase
Solution Approach 1:
The conduit system is segmented into three distinct parts with the pump positioned at a strategic connection point. This segmentation reduces the overall length of double-walled insulated conduits required and minimizes the number of fittings needed, thereby reducing system complexity and cost while maintaining reliable hydrogen delivery.
Solution Approach 2:
The pump is positioned to serve multiple functions: it pressurizes hydrogen from the fuel tank and provides a connection point for the conduit system. By locating the pump near the fuel tank rather than near the turbomachine, the system reduces conduit length and fitting requirements, making the system more efficient and less complex.
3Power
If the pump is positioned far from the fuel tank, then the hydrogen can be pressurized closer to the heat exchanger, but the conduit length from the fuel tank to the pump increases causing weight increase
Solution Approach 1:
The pump is positioned as an intermediary component near the fuel tank, serving as the first connection point in the hydrogen supply chain. This positioning minimizes the length of the first conduit from the fuel tank to the pump, reducing conduit weight while still allowing effective pressurization of the hydrogen before it travels through the second conduit to the heat exchanger.
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 minimizes the length of double-walled conduits, reduces onboard weight, and lowers the risk of icing, while optimizing hydrogen temperature for turbomachines, thereby enhancing the efficiency and reducing costs.
Implementation Method 1
at least one heat exchanger configured to exchange calories between hydrogen and a heat transfer fluid from at least one source present in the aircraft
Implementation Method 2
the conduits are complex, thermally insulated double-walled ducts, with the area between the two walls being inert or evacuated
Data Source
Figure 1~2
Figure 3~8
Figure 9~10
AI summary
The invention relates to an aircraft comprising: - a fuselage (32), - a wing (34), - at least one hydrogen-powered turbomachine (40) generating thrust at a propulsion unit (36) located away from the fuselage (32), - at least one fuel tank (46) positioned in the fuselage (32) and configured to store hydrogen in a cryogenic state, - at least one hydrogen supply system connecting the fuel tank (46) and the turbomachine (40) comprising: o at least one pump (50) positioned in the fuselage (32) near the fuel tank (46), o at least one hydrogen heating system (52) positioned in the fuselage (32) near the pump (50). This solution makes it possible to reduce the length of the complex double-walled conduits configured to channel the hydrogen in a cryogenic state between the fuel tank and the hydrogen heating system.