초록 ▼

A diverging rocket engine nozzle has a system to allow ambient gases to flow from the outside to the inside of the nozzle\s chamber. The system includes a plurality of coolant conduits adjacent the inside surface of the nozzle. The conduits are spaced apart to provide a plurality of vent openings wh

A diverging rocket engine nozzle has a system to allow ambient gases to flow from the outside to the inside of the nozzle\s chamber. The system includes a plurality of coolant conduits adjacent the inside surface of the nozzle. The conduits are spaced apart to provide a plurality of vent openings which extends from the inside to the outside of the nozzle\s chamber. A plurality of valves controls gas flow through the vent passages when the pressure outside of the nozzle is greater than the pressure directly adjacent the inside surface of the nozzle. The coolant conduits cool and shield the valves at their points of attachment to the outside of the nozzle.

대표청구항 ▼

A rocket nozzle structure for a rocket engine which has a flowpath for rocket gases extending axially through the nozzle, the nozzle structure including a casing having an exterior and having an interior which bounds the flowpath, the casing having a throat and a divergent region extending downstrea

A rocket nozzle structure for a rocket engine which has a flowpath for rocket gases extending axially through the nozzle, the nozzle structure including a casing having an exterior and having an interior which bounds the flowpath, the casing having a throat and a divergent region extending downstream from the throat, the divergent region having a high expansion ratio, and which comprises: a casing having a divergent region, the casing including an inner wall having a plurality of conduits for coolant which bound the flowpath for rocket gases, at least two of the conduits being spaced apart leaving an opening therebetween, a plurality of vent passages extending from the exterior of the casing to the interior of the casing each vent passage extending through an associated opening between a pair of conduits; an outer member attached to the inner wall which is adapted to support a seal element, the outer member being spaced by the conduits from the flowpath for rocket gases, a plurality of seal elements, each of which is adjacent to at least one vent passage, the seal element extending axially from outer member of the casing and having a first end attached to the outer member and a second end movable between an open position which permits flow through the vent passage from the exterior to the interior and a closed position which blocks flow through the passage from the interior to the exterior, the seal element having a first side facing the exterior of the nozzle and a second side facing the interior of the nozzle; wherein each seal element is movable to the open position to permit flow through the passage under operative conditions having separated flow adjacent the casing at which the pressure in the exterior is greater than the pressure on the interior to stabilize the location of the separated flow and is movable to the closed position to block flow through the passage under operative conditions having full flow adjacent the casing at which the pressure adjacent the casing on the interior is greater than the pressure on the exterior and wherein each seal element at its point of attachment to the outer member is shielded by the coolant conduits from the rocket gases and is cooled by the coolant passing through the coolant conduits.