A gas turbine engine has a fuel system including an apparatus. The apparatus includes a housing containing at least a fuel filter assembly and a bypass valve assembly within the housing. The bypass valve assembly selectively opens or closes a bypass passage which bypasses a filtering unit of the fuel filter assembly. In accordance with one aspect, respective first and second fuel flows are introduced into the housing to be merged and mixed therein prior to entering the fuel filter assembly or the bypass valve assembly. In accordance with another aspect, an ice accretion device is provided within the housing to allow ice formation and accumulation thereon as a result of a transient icing occurrence when the mixed fuel flows in the housing pass through the ice accretion device to enter the fuel filter assembly.
Fuel filter and bypass valve arrangement
2018-07-17
Patent
Elektronische Ressource
Englisch
IPC: | B01D SEPARATION , Trennen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02M Zuführen von Brennstoff-Luft-Gemischen oder deren Bestandteilen bei Brennkraftmaschinen allgemein , SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF |
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