Fuel conditioning system for powering an aircraft turbomachine and associated method

Abstract

A fuel conditioning system (SC) for supplying an aircraft propulsion system (M) comprises: a pressure sensor (6) configured to be mounted on a fuel outlet (20) of a fuel tank (2) and to determine a measured pressure (Pm) of a fuel flow (Q); a heating device (7) configured to be mounted on the storage tank (2) so as to heat the fuel (Q) directly in the storage tank (2); and a computer (9) configured to determine a quantity of heat (W) to be supplied to the heating device (7) from a difference between the measured pressure (Pm) and an injection pressure (Pi), so as to introduce, from an inlet point (11) of a fuel circuit (1), a fuel flow (Q) directly in a gaseous state and under a pressure determined to reach the injection pressure (Pi) at the outlet point (12) of the fuel circuit (1). Abstract Figure: Figure 2