Societe Europeenne De Propulsion

Societe Europeene De Propulsion

Andre Beaurain

Etienne Tiret

Didier Vuillamy

Pierre Desclos

Jean-Robert Lehe

Pierre-Andre Baudart

Rene Bosson

Martin Sion

Claude E Bonniot

Jean-Paul Dumont

Claude Pacou

The invention relates to a method of manufacturing an enclosure containing hot gases cooled by transpiration. The enclosure comprises a porous wall and means for applying a cooling fluid to the outside face of the porous wall to cause a flow of cooling fluid to pass through the porous wall by transpiration. The cooling fluid application means is formed by disposing a plurality of cooling liquid distribution pipes regularly around the porous wall and terminating tangentially on its outside face in a plurality of superposed horizontal injection levels. Feed channels are provided crossing substantially perpendicularly through the distribution pipes, formed between each of them, and connected to cooling liquid feed means. Calibration ducts of determined section are provided, connecting, at each of the injection levels, the vertical feed channels to the horizontal distribution pipes surrounding them, to deliver predetermined headloss to the inside face of the porous wall. The headloss is adapted as a function of the zone to be cooled to optimize cooling flow rates along the porous wall.

Method of manufacturing a combustion enclosure with cooling by

The invention relates to an enclosure containing hot gases cooled by transpiration, the enclosure comprising a porous wall and means for applying a cooling fluid to the outside face of said porous wall so as to cause a flow of cooling fluid to pass through the porous wall, by transpiration. The cooling fluid application means comprise a plurality of cooling liquid distribution pipes regularly disposed around the porous wall and terminating tangentially on its outside face in a plurality of superposed horizontal injection levels, and feed channels crossing substantially perpendicularly through the distribution pipes, formed between each of them, and connected to cooling liquid feed means, together with calibration ducts of determined section connecting, at each of the injection levels, the vertical feed channels to the horizontal distribution pipes surrounding them so as to deliver predetermined headloss to the inside face of the porous wall, which headloss is adapted as a function of the zone to be cooled so as to optimize cooling flow rates along the porous wall.

Combustion enclosure with cooling by transpiration

Injection system with concentric slits and the associated injection

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.

Rocket engine nozzle with an engine diffuser

In a rocket engine nozzle with a selectively smaller outlet cross-section, the nozzle comprising a converging 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 defining a high cross-section ratio, a releasable annular obstacle is connected to the downstream end of the diverging part so as to define at the outlet of the diverging part a zone of selectively smaller cross-section which ensures stability of the separation of the flow of hot gases relative to the wall of the diverging part during a first phase of flight.

Rocket engine nozzle with selectively smaller outlet cross-section

In a rocket engine nozzle comprising: a converging portion that receives the gases produced in a combustion chamber; a throat of small section; and a diverging portion connected to the nozzle throat; the diverging portion includes a set of downstream notches running longitudinally from its downstream end and uniformly distributed around the entire periphery of the diverging portion, the total width of all of the notches within any section representing about 1% to 6% of the periphery of the diverging portion. The notches serve to avoid having a jet separation line that is irregular and unstable, and they facilitate matching the diverging portion to ambient conditions that vary in flight.

Rocket engine nozzle having a notched diverging portion

The centrifugal pump with an open-faced impeller comprises at least one open-faced impeller having blades placed inside a casing defining both a delivery pipe and a suction pipe facing the base of the blades situated in the vicinity of a central shaft for driving the impeller. An active axial balancing system for the rotary assembly is integrated in the impeller and comprises a balancing chamber interposed between the rear face of the body of the impeller and an outer rear portion of the casing, the impeller itself acting as the balancing turntable. A shroud-forming intermediate part is prevented from rotating relative to the casing and is interposed between an outer front portion of the casing and the impeller, a cavity is formed between the outer front portion of the casing and the intermediate part to receive a back pressure of predetermined value serving, in operation, to maintain small clearance without contact between the intermediate part that is prevented from rotating and the blades of the impeller.

High performance centrifugal pump having an open-faced impeller

The rocket engine is fitted with an injection device comprising a single injection plate having a central portion that defines the end of the burn zone of the combustion chamber and that contains first propellant injectors having a high mixing ratio adapted to the conditions under which hot gases are produced in the burn zone, and a peripheral portion in the form of a ring that defines the end of an annular cavity of a gas generator and that contain second propellant injectors having a low mixing ratio and adapted to the conditions under which hot gases are produced in the gas generator. The gas generator is thus integral with the combustion chamber and the annular cavity of the gas generator is separated from the burn zone of the combustion chamber by a cylindrical wall that extends axially perpendicularly to the injection plate and that is fixed thereto in sealed manner.

Liquid propellant rocket engine with parallel auxiliary flow, and an

A compact high power turbopump for feeding liquid propellant to a rocket engine comprises: a short, large diameter shaft that is capable of rotating; a single impeller providing a large pressure rise at a large flow rate, the impeller being mounted on the short shaft so as to constitute a single pump stage; a ball bearing for supporting the short shaft in a small section zone thereof situated in front of the impeller; a fluid bearing dimensioned so as to withstand a high speed of rotation N and having a large diameter D, the fluid bearing serving to support the short shaft in a large section zone situated behind the impeller; a turbine cantilevered out on the short shaft behind the fluid bearing; an inducer of the high pressure type disposed upstream from the ball bearing on the suction pipe; and metal casing elements for the pump and for the turbine that are of simplified shape.

Compact high power turbopump for a rocket engine

A centrifugal pump with an open-faced impeller for conveying a working liquid, the pump comprising at least one open-faced impeller provided with blades placed inside a casing defining a suction pipe facing the bottoms of the blades in the vicinity of a central shaft that drives the impeller and forming a part of a rotary assembly, and a delivery pipe fitted with a fixed diffuser disposed facing the peripheral ends of the blades. An active axial balancing system for the rotary assembly, which balancing system is integrated in the impeller and comprises a balancing chamber interposed between the rear face of the body of the impeller and an outer rear portion of the casing. The balancing chamber communicating with the delivery pipe via a first nozzle whose axial clearance is kept invariable in operation and which is defined by the peripheral end of the impeller itself acting as a balancing turntable, and a nozzle piece secured to the outer rear portion of the casing and interposed between the diffuser and said peripheral end of the impeller. The balancing chamber communicating directly or indirectly with the suction pipe of the pump via a second nozzle.

Growing community of inventors

Chambly, France

Andre Beaurain