发明名称 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
摘要 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 60C, 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
申请公布号 RU2383765(C1) 申请公布日期 2010.03.10
申请号 RU20080130729 申请日期 2008.07.24
申请人 FEDERAL'NOE GOSUDARSTVENNOE UNITARNOE PREDPRIJATIE "NAUCHNO-ISSLEDOVATEL'SKIJ INSTITUT POLIMERNYKH MATERIALOV" 发明人 SHAJKHUTDINOV RASHID VAGIZOVICH
分类号 F02K9/24;F23G7/00 主分类号 F02K9/24
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