Patent ID: 11920606
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A fuel pump for an aircraft engine, comprising:
an inducer comprising an axis of rotation;
a centrifugal impeller coaxial with the inducer, the inducer being fixed to the centrifugal impeller upstream thereof so as to define an annular interface between the inducer and the centrifugal impeller about the axis of rotation, the annular interface comprising an annular space spacing axially the inducer and the centrifugal impeller, and two contact portions between the inducer and the centrifugal impeller disposed radially outside the annular spaced; and
a first plenum chamber and a second plenum chamber, in which the inducer and the centrifugal impeller are spaced axially from each other, each being disposed circumferentially between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed circumferentially about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the centrifugal impeller at the other end.