The invention relates to a motive flow valve (30) for aircraft engine comprising: a shaft (31) comprising a high-pressure chamber (36), a low-pressure chamber (33), a fuel inlet (42), a fuel outlet (44), and a shoulder (45) arranged between the fuel inlet and the fuel outlet, defining an abutment surface (46), a drawer (55) configured to be displaced relatively to the shaft under the effect of a difference in pressure between the high- and low-pressure chambers, between a closed position wherein the drawer abuts with the abutment surface in the closed position and obstructs the fuel inlet, and an open position wherein the drawer releases the fuel inlet, with the drawer comprising a portion extending into an intermediate chamber (39), the drawer further comprising a channel (62) exiting on the one hand in a first portion (63) of the intermediate chamber and communicating with the fuel outlet in the open and closed positions, and on the other hand in a second portion (64) of the intermediate chamber that does not communicate with the fuel inlet or with the fuel outlet in the open and closed positions, and a sealing element (59) interposed between the abutment surface and the drawer in the closed position.


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    Titel :

    Valve for fuel circuit of an aircraft engine


    Beteiligte:

    Erscheinungsdatum :

    2016-08-30


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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