Snecma

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Arianegroup Sas

Jean-Michel Nguyen Duc

Sébastien Boufflert

François Danguy

Alban Lemaitre

Laurent Fabbri

Fabien Tessier

Fabien Wahl

Cëdric Sene

Philippe Geai

Jean-Marie Duchemin

Simon Menager

Cédric Sene

The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump () comprising at least: an impeller (); a rotary shaft () secured to said impeller (); a casing () having an axial admission passage (); at least one first bearing () supporting said rotary shaft () in said casing (); and at least one dynamic seal () around the rotary shaft (), the impeller () being situated between the at least one dynamic seal () and the axial admission passage () of the pump (). The centrifugal pump () also comprises, between the impeller () and at least one dynamic seal (), an axial force compensation disk () secured to the shaft () and presenting a diameter greater than 70% of a diameter of the impeller (). A front face () of the disk () faces towards the impeller () and is connected to a branch connection for fluid under pressure taken downstream from the pump (), and a rear face () faces towards the dynamic seals () and presents fins () that are oriented radially, at least in part.

Centrifugal pump, in particular for supplying power to rocket engines

A suction stage for a pump with a centrifugal wheel, the suction stage including a rotational impeller equipped with a hub and arranged upstream of the centrifugal wheel, the suction stage further including a diffuser arranged between the impeller and the centrifugal wheel, the diffuser including a plurality of blades. The hub has a downstream surface extending axially so as to converge toward the centrifugal wheel, and the blades of the diffuser have free ends, the blades protruding radially toward the downstream surface.

Impeller and diffuser with a rotating and converging hub

The fluid transfer device comprises a stator assembly incorporating a plurality of return channels which pick up the high speed fluid flow leaving a centrifugal impeller of one stage of the turbomachine for the purpose of rectifying, slowing down, and conveying said flow to the inlet of another centrifugal impeller of an adjacent stage of the turbomachine. Each return channel is constituted by a continuous shaped individual tubular element. A first continuous return channel is defined by a set of varying sections defined by parameters and extending normally to a mean line situated in a predefined plane (P,P,P,) containing the axis of the machine. The mean line has a rectilinear first portion, a curved second portion forming a circular arc of radius R,, and a rectilinear third portion. The various return channels are identical and can be derived one from another by rotation about the axis of the turbomachine.

Device for transferring fluid between two successive stages of a multistage centrifugal turbomachine

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Vezillon, France

Jean-Michel Nguyen Duc