Yaw the change propulsive mechanism opening reliability growth test device of pitching engineĭouble atomization pintle ejector filler suitable for high-viscous liquidĪ kind of oblique slot type pintle ejector filler head construction Hybrid rocket engine pintle formula becomes larynx footpath Effuser deviceĪ kind of welding method of pintle formula ejector fillerĪ kind of pre- rotating pintle ejector filler applied to double elements liquid-propellant rocket engine The coaxial pintle formula ejector filler thrust chamber of a kind of flutingĪpplications Claiming Priority (1) Application Numberįamily ID=52223636 Family Applications (1) Application NumberĬited By (21) * Cited by examiner, † Cited by third party Publication number Priority Applications (1) Application Number CN201410264384.8A The coaxial pintle formula ejector filler thrust chamber of a kind of fluting one fluting coaxial needles hydrant ejector filler thrust chamber according to claim 1, is characterized in that: described central tube lower end is provided with termination notch Termination notch is made up of major trough and auxiliary groove Described major trough height is higher than auxiliary groove, and auxiliary well width is wider than major trough. Owing to relying on ejector filler organizationally efficiently to burn, reached the target in reliable cooling body portion again by impinging jet optimization, thus technical difficulty is larger.In order to realize the high performance target of current precise tracking high thrust fast-response, develop two sleeves " face shutdown " the pintle formula thrust chamber structure of the fluting spray structure that a kind of nothing cools specially.The Central Fuel fluting scheme of two sleeve is adopted to make center propellant with pencil jet and outer ring propellant agent liquid film colliding, not only increase fuel and oxidising agent area, enhance jet partial penetration ability, make part pencil jet more easily penetrate outer ring liquid film, formed the various flows of spatially (radial with axially) by force, proportions of ingredients distribute to be irregularly staggered, synthesizing jet-flow that firing angle is different be for can effectively reduce border area temperature.Ģ. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Application filed by 11 Research Institute of 6th Academy of CASC filed Critical 11 Research Institute of 6th Academy of CASC Priority to CN201410264384.8A priority Critical patent/CN104234870B/en Publication of CN104234870A publication Critical patent/CN104234870A/en Application granted granted Critical Publication of CN104234870B publication Critical patent/CN104234870B/en Status Active legal-status Critical Current Anticipated expiration legal-status Critical Links Original Assignee 11 Research Institute of 6th Academy of CASC Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)ġ1 Research Institute of 6th Academy of CASC ( en Inventor 凌前程 高坤 林革 李军 刘新华 章荣军 宋大亮 种衡阳 刘永兴 丰雪平 Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Granted Application number CN201410264384.8A Other languages Chinese ( zh) Google Patents Slotted coaxial pintle type injector thrust chamberĭownload PDF Info Publication number CN104234870A CN104234870A CN201410264384.8A CN201410264384A CN104234870A CN 104234870 A CN104234870 A CN 104234870A CN 201410264384 A CN201410264384 A CN 201410264384A CN 104234870 A CN104234870 A CN 104234870A Authority CN China Prior art keywords central tube thrust chamber inner sleeve outer sleeve sleeve Prior art date Legal status (The legal status is an assumption and is not a legal conclusion. Google Patents CN104234870A - Slotted coaxial pintle type injector thrust chamber CN104234870A - Slotted coaxial pintle type injector thrust chamber
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