Rocket engine nozzle with an engine diffuser
AssigneeSociete Europeenne de Propulsion
InventorsClaude Bonniot, Didier Vuillamy, Pierre Desclos, Etienne Tiret, Andre Beaurain
Life of this patent
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Abstract
The downstream portion of the diverging part of the nozzle of the rocket engine is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the presence of significant outside pressure to recompress the flow of hot gases and to prevent a flow separation from appearing along with the wall of the diverging part. The ejectable diffuser may have a streamlined throat which constitutes the zone of smaller cross-section.
Claims10
A rocket engine nozzle of the first stage of a launcher with an ejectable diffuser, comprising a convergent portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the nozzle throat and terminating at its downstream portion in a gas jet outlet cross-section which defines a high cross-section ratio greater than about 50,
- wherein the downstream portion of the diverging part is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the presence of significant outside pressure to recompress the flow of hot gases and to prevent a flow separation from appearing along the wall of the diverging part.
A rocket engine nozzle of the first stage of a launcher with an ejectable diffuser, comprising a convergent portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the nozzle throat and terminating at its downstream portion in a gas jet outlet cross-section which defines a high cross-section ratio greater than about 50,
- wherein the downstream portion of the diverging part is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the presence of significant outside pressure to recompress the flow of hot gases and to prevent a flow separation from appearing along the wall of the diverging part, and
- wherein the inside surface of the diverging part includes longitudinal ribs which extend beyond its downstream end and co-operate with longitudinal grooves formed on the inside surface of the releasable diffuser.
A rocket engine nozzle of the first stage of a launcher with an ejectable diffuser, comprising a convergent portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the nozzle throat and terminating at its downstream portion in a gas jet outlet cross-section which defines a high cross-section ratio greater than about 50,
- wherein the downstream portion of the diverging part is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the presence of significant outside pressure to recompress the flow of hot gases and to prevent a flow separation from appearing along the wall of the diverging part, and
- wherein the inside surface of the releasable diffuser includes longitudinal ribs which extend beyond the downstream end of the diffuser and co-operate with longitudinal grooves formed on the inside surface of the diverging part.
A rocket engine nozzle of the first stage of a launcher with an ejectable diffuser, comprising a convergent portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the nozzle throat and terminating at its downstream portion in a gas jet outlet cross-section which defines a high cross-section ratio greater than about 50,
- wherein the downstream portion of the diverging part is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the presence of significant outside pressure to recompress the flow of hot gases and to prevent a flow separation from appearing along the wall of the diverging part, and
- wherein the means for connecting the releasable diffuser to the downstream end of the diverging part comprise an assembly of hinged clamps which grip flanges formed at the contacting ends of the diverging part and of the releasable diffuser, and a retaining system for the clamps which is equipped with unlocking means selectively controllable to allow release of the diffuser once the risk of separation of the gas jet inside the diverging part has passed.
Dependencies are inferred from the claim text.