Patent ID: 11905883
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A fuel supply circuit for a combustion chamber of a turbomachine, comprising:
a fuel supply pump configured to provide a fuel flow at a predetermined flow rate,
a plurality of fuel injectors,
an injector connection line for connecting the fuel supply pump to the plurality of fuel injectors, and
a device for thermally treating the fuel flow comprising a chamber connected to a fuel inlet connected to the fuel supply pump and to a fuel outlet connected to the injector connection line, heating elements being located in the chamber and being configured to heat the fuel flow provided by the fuel supply pump up to a predetermined temperature so as to cause a coking of the fuel flow within the chamber,
wherein said heating elements comprise at least one perforated metal tube which comprises fuel passage orifices and which is associated with a respective heating electrode for heating the at least one perforated metal tube and thus the fuel flow passing through the at least one perforated metal tube,
wherein the at least one perforated metal tube is formed of a plurality of metal sub-tubes nested concentrically inside each other,
wherein each metal sub-tube is perforated and comprises the fuel passage orifices,
wherein each metal sub-tube is heated by the respective heating electrode,
wherein a gap between proximate walls of proximate metal sub-tubes forms a fuel passage.