LIQUID PROPELLANT ROCKET ENGINE CHAMBER NOZZLE Russian patent published in 2015 - IPC F02K9/97 

Abstract RU 2563114 C1

FIELD: engines and pumps.

SUBSTANCE: claimed nozzle comprises outer and inner shells that make the cooling duct communicated via submanifold ring with coolant feed manifold arranged at outer shell. Said manifold comprises two diametrically opposite pipes and at least one crosswise barraged at equal angular distance from the axes of said pipes. Said web overlaps 80-90% of the manifold cross-section area to make the gap between the web and submanifold ring. Besides, engine combustion chamber nozzle is equipped with coolant discharge manifold with three coolant discharge pipes equally spaced apart in circle.

EFFECT: higher reliability of nozzle, decreased overall dimensions and weight of coolant feed and discharge manifolds.

3 cl, 4 dwg

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RU 2 563 114 C1

Authors

Jakushin Nikolaj Ivanovich

Danil'Chenko Valerij Pavlovich

Mikhajlov Stepan Vasil'Evich

Lavrov Valerij Nikolaevich

Faridonov Rail' Rashitovich

Dates

2015-09-20Published

2014-05-19Filed