Snecma

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

Noël David

Alain Pyre

Nicolas Ravier

Olivier Dobek

Philippe Geai

Michel Fiolek

Jacques Lelong

Romain Stephant

Claude Pomies

Philippe Morel

A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine

A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.

Convex thermal shield for rocket engine with extendable divergent nozzle

The fastener fitting () has a first fastener zone () for fastening to an element () of the deployment mechanism. This fastener fitting () has two longitudinal arms (A,B) that extend substantially in parallel and in the same direction from the first fastener zone (). The free ends of these arms that are remote from the first fastener zone are separate, with each arm being provided with a distinct fastener surface (A,B), these respective fastener surfaces together forming the second fastener zone.

Fastener fitting between the movable portion of a deployable diverging bell for a thruster and a mechanism for deploying said movable portion

Inducer equipment adapted to a pump having large induction capacity which cludes a case surrounding an inducer rotor having a plurality of blades leaving clearance relative to the case. The clearance between the peripheral portions of the blades and the case is of an increased value greater than the value of the normal clearance over a zone which extends both into a cylindrical first portion of the inside wall of the case upstream from the inducer rotor and into a portion of the inside wall of the case adjacent to the cylindrical first portion and overlapping an upstream portion of the inducer rotor over a distance from the leading edges of the blades of the inducer rotor. The ratio between the clearance of increased value and the clearance of normal value is advantageously greater than 10.

Inducer equipment for a pump having large induction capacity

Growing community of inventors

Breuilpont, France

Noël David