| 引用本文: | 陈杰,王克昌,陈启智.液氧/煤油推进剂液体火箭发动机循环动力平衡分析.[J].国防科技大学学报,1992,14(2):53-58.[点击复制] |
| Chen Jie,Wang Kechang,Chen Qizhi.Cycle Power Balance Analysis for Liquid Rocket Engine with LO2/RP-l Propellant Combination[J].Journal of National University of Defense Technology,1992,14(2):53-58[点击复制] |
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| 液氧/煤油推进剂液体火箭发动机循环动力平衡分析 |
| 陈杰, 王克昌, 陈启智 |
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(航天技术系)
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| 摘要: |
| 本文对以液氧/煤油为推进剂的发生器循环和分级燃烧循环方案进行了分析，求出了各种循环方案的最大室压，给出了室压、推力、燃烧室混合比和喷管出口直径对发动机比冲和系统平衡参数的影响，并探讨了平衡参数对效率、涡轮压比和发生器（或预燃室）混合比等设计参数变化的敏感性。 |
| 关键词: 液体推进剂火箭发动机，动力循环分析 |
| DOI： |
| 投稿日期：1991-03-12 |
| 基金项目: |
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| Cycle Power Balance Analysis for Liquid Rocket Engine with LO2/RP-l Propellant Combination |
| Chen Jie, Wang Kechang, Chen Qizhi |
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(Department of Aerospace Technology)
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| Abstract: |
| The gas generator cycle and staged combustion cycle with LO2/RP-1 propellants combination have been analyzed in this paper. The maximum combustion chamber pressure for various cycles has been found. The effect of combustion chamber pressure，sea level thrust，chamber mixture ratio，nozzle exit diameter on engine specific impulse and system balance parameters is given. The sensitivity dependences of effeciences，turbine pressure ratio，gas generator (or preburner) mixture ratio and other design parameters on balance parameters have been investigated |
| Keywords: liquid propellant rocket engines,cycle power balance analysis |
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