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2 540 190

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(51)

IPC

F02K9/97(2006-01-01)

F02K9/95(2006-01-01)

(21) (22)

Application

2013157814/06, 2013-12-26

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Start date

2013-12-26

(22)

Actual filing date

2013-12-26

(45)

Published

2015-02-10

(72)

Inventor

Makarovets Nikolaj AleksandrovichAljazhedinov Vadim RashitovichZakharov Oleg L'VovichKashirkin Aleksandr AleksandrovichErokhin Vladimir Evgen'EvichBazarnyj Aleksej Nikolaevich

(73)

Holder

Otkrytoe Aktsionernoe Obshchestvo Ob"Edinenie

SOLID-PROPELLANT ROCKET ENGINE NOZZLE Russian patent published in 2015 - IPC F02K9/97 F02K9/95

Abstract RU 2540190 C1

FIELD: engines and pumps.

SUBSTANCE: proposed nozzle comprises case, subsonic and supersonic parts and seal-and-start device with afterburner tube and support. Flat swirler is arranged in said afterburner tube perpendicular to its axis at a distance from outlet cross-section at rigid mounts. Lengthwise axes of the latter are located in planes extending through afterburner tube axis. Flat swirler is provided with one or several bores and lining with low ablation temperature fitted at its front end surface.

EFFECT: decreased scatter of internal ballistic parameters at acceleration.

3 cl, 1 dwg

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RU 2 540 190 C1

Authors

Makarovets Nikolaj Aleksandrovich

Aljazhedinov Vadim Rashitovich

Zakharov Oleg L'Vovich

Kashirkin Aleksandr Aleksandrovich

Erokhin Vladimir Evgen'Evich

Bazarnyj Aleksej Nikolaevich

Dates

2015-02-10—Published

2013-12-26—Filed