The transition to zero carbon fuels, such as hydrogen, for aircraft propulsion is considered the most effective solution to reduce CO 2 emissions in the aviation sector. This transition is a key objective of the European Green Deal and Flight Path 2050. One of the main challenges in using hydrogen is its low density, making cryogenic storage the most effective solution for the aeronautic applications. The fuel must be delivered to the combustion chamber at specific pressure and temperature conditions and is therefore used as a heat sink for various thermal loads. This work presents a possible design for a fuel system of an aircraft turbine. The system has been designed using a lumped parameter numerical modelling approach. Different types of heat exchangers have been selected based on fluid and available thermal load. Additionally, an auxiliary fuel system is proposed, incorporating a secondary smaller tank and a compressor to manage residual gaseous hydrogen when the turbine is shut down and to facilitate cold starts. Finally, a control logic for both the main and auxiliary fuel systems has been developed and tested under different working conditions. In developing this model, special attention has been given to parametrization: the geometry and dimensions of heat exchangers are easily adjustable by modifying a few key parameters, allowing for quick adaptations in pursuit of geometric optimization.
A lumped parameter model of fuel system and heat exchangers for a hydrogen-powered aircraft turbine engine
Li Veli, Stefano;Rosario Apuzzo, Alfonso;Frosina, Emma;
2025-01-01
Abstract
The transition to zero carbon fuels, such as hydrogen, for aircraft propulsion is considered the most effective solution to reduce CO 2 emissions in the aviation sector. This transition is a key objective of the European Green Deal and Flight Path 2050. One of the main challenges in using hydrogen is its low density, making cryogenic storage the most effective solution for the aeronautic applications. The fuel must be delivered to the combustion chamber at specific pressure and temperature conditions and is therefore used as a heat sink for various thermal loads. This work presents a possible design for a fuel system of an aircraft turbine. The system has been designed using a lumped parameter numerical modelling approach. Different types of heat exchangers have been selected based on fluid and available thermal load. Additionally, an auxiliary fuel system is proposed, incorporating a secondary smaller tank and a compressor to manage residual gaseous hydrogen when the turbine is shut down and to facilitate cold starts. Finally, a control logic for both the main and auxiliary fuel systems has been developed and tested under different working conditions. In developing this model, special attention has been given to parametrization: the geometry and dimensions of heat exchangers are easily adjustable by modifying a few key parameters, allowing for quick adaptations in pursuit of geometric optimization.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
