METHOD TO REDUCE EFFECTS OF SHOCK WAVE AND MIXED STEAM-GAS FLOW PARAMETRES IN LOCALISATION, COOLING AND NEUTRALISATION CHAMBER AND GAS INTAKE INCORPORATING GAS DUCT IN LIQUIDATING ROCKET SOLID-PROPELLANT CHARGE AND DEVICE TO THIS END Russian patent published in 2010 - IPC F02K9/24 F23G7/00 

Abstract RU 2383765 C1

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises monitoring and controlling combustion product exhaust thermal conditions. Note here that a gas intake is used comprising two compartments. When shock wave and mixed steam-gas flow pass through said gas intake, aforesaid mixed flow is additionally cooled by coolant, i.e. water or neutralising solution fed via distributing circular manifold with spraying nozzles to 60°C, max. Another invention of proposed set relates to gas intake that comprises gas duct, water treatment system and two compartments communicated via opening to form labyrinth. Said opening makes 1/4 of the compartment circumference length. To improve conditions for mixed steam-gas flow to enter gas intake second compartment, the latter is turned through 110° to 120° relative to gas duct axis. Total inner volume of semi-enclosed space of two gas duct two compartments exceeds the volume of formed combustion products by 3 to 5 times in solid propellant charge being liquidated.

EFFECT: reduced shock wave effects, higher efficiency of gaseous hydrogen chloride dissolution.

3 cl, 7 dwg

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RU 2 383 765 C1

Authors

Shajkhutdinov Rashid Vagizovich

Dates

2010-03-10Published

2008-07-24Filed