Liquid Hydrogen Fuel Distribution System Performance for Short Medium Range Civil Aircraft
Typ
Examensarbete för masterexamen
Program
Applied mechanics (MPAME), MSc
Publicerad
2022
Författare
Azimi, Ali
Modellbyggare
Tidskriftstitel
ISSN
Volymtitel
Utgivare
Sammanfattning
Aviation is one of the most prominent parts of the transportation sector nowadays,
and its share is growing globally, so it is necessary to reduce its emissions. The
EU plan for net zero emissions by 2050 needs to be considered for civil aircraft as
well. One of the most practical solutions for aviation emissions reduction is to use
other options than fossil fuels, like liquid Hydrogen. This project is based on the
Airbus model A321 as a twin-engine civil aircraft candidate. Liquid Hydrogen is
in cryogenic condition (22K, 1.6bar), and it needs to be pumped during Maximum
Take-Off (MTO) to a pressure of 40.6 bar in the combustion chamber. The pressure
rise duty from the tank to the high-pressure pump must be done by two pumps
in the fuel line a booster pump and a high-pressure pump. This study has two
parts, the first concerns the fuel system design, and the second part comprises the
design of the booster pump. We have designed the fuel system as a general study
to see what components have to be through the fuel line from the tank to the
high-pressure pump. These components include the pipeline to carry the liquid
Hydrogen, valves for different roles in the system, and fitting for pipeline joints or
direction changes. The booster pump is responsible for delivering the fuel from
the tank to the fuel lines. According to Brewer’s study [1], this booster pump can
be of the centrifugal type with specific boundary conditions for design. The pump
inlet/outlet boundary conditions are the direct results of the real gas modeling using
CoolProp. CoolProps helps us to determine the properties of the LH2 at a given
location in the fuel system stage to obtain preliminary values for the booster pump
design. MTO is the booster pump design point for this research delivering a mass
flow of 0.298 kg/s at a rotational speed of 12312 RPM. The CFD simulation is done
using the ANSYS2021R1 package via the CFX solver. The values for preliminary
design are used to generate the blade geometry, using Vista CPD and BladeGen.
We have also considered off-design simulations for different points by changing mass
flow/rotational speed to create a performance curve for the booster pump. This
study includes the CFD design for the booster pump as the only component in
which we assessed the preliminary design.
Beskrivning
Ämne/nyckelord
Booster Pump, Cryogenic, Hydrogen, MTO