Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector

Nobuyuki Yatsuyanagi

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Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector

机译：同轴喷油器LOX /液甲烷蓄冷冷却器的综合设计方法

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摘要

A comprehensive design method for a LOX/Liquid-Methane (L-CH_4) rockel engine combustor with a coaxial injector and the preliminary design of the regenerative cooling combustor with 100-kN thrust in vacuum at a combustion pressure of a 3.43 MPa are presented. Reasonable dimensions for the combustor that satisfy the targeted C~* efficiency of more than 98% and combustion stability are obtained.

机译：提出了一种具有同轴喷油器的LOX /甲烷（L-CH_4）岩石发动机燃烧器的综合设计方法，以及在3.43 MPa的燃烧压力下具有100kN真空推力的蓄冷式燃烧器的初步设计。获得了满足目标C〜*效率超过98％和燃烧稳定性的合理尺寸的燃烧室。

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来源
《Transactions of the Japan society for aeronautical and space sciences》 |2009年第177期|180-187|共8页
作者
Nobuyuki Yatsuyanagi;
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作者单位

Kakuda Research Center, National Aerospace Laboratory, Kakuda, Japan;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类
关键词
LOX/liquid-methane rocket engine; LOX/LNG rocket engine; coaxial injector; C~* efficiency; combustion stability;

机译：LOX /液甲烷火箭发动机;LOX / LNG火箭发动机;同轴注射器C〜*效率;燃烧稳定性;

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1. Establishment Of Design Method For Liquid Hydrogen Regenerative Cooling Combustor Of Lox/hydrogen Rocket Engine [J] . Nobuyuki Yatsuyanagi Transactions of the Japan society for aeronautical and space sciences . 2009,第174期

机译：Lox /氢火箭发动机液态氢蓄冷冷却器设计方法的建立
2. Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine: Evaluation of Design for Injectors of the LE-5 Engine and Its Derivatives [J] . Nobuyuki Yatsuyanagi Transactions of the Japan society for aeronautical and space sciences . 2007,第169期

机译：LOX /氢火箭发动机同轴喷油器的设计标准研究：LE-5发动机及其衍生物喷油器的设计评估
3. Injector-coupled thermoacoustic instabilities in an experimental LOX-methane rocket combustor during start-up [J] . CEAS Space Journal . 2020,第2期

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4. Euler-Lagrange Simulation of a LOX/H2 Model Combustor with Single Shear Coaxial Injector [C] . Markus Lempke, Peter Gerlinger, Michael Rachner, Annual results and review workshop on high performance computing in science and engineering . 2011

机译：单剪切同轴喷油器的LOX / H2型燃烧器的Euler-Lagrange模拟
5. Minimizing Hydraulic Losses in Additively-Manufactured Swirl Coaxial Rocket Injectors via Analysis-Driven Design Methods [D] . Morrow, David. 2020

机译：通过分析驱动的设计方法将涡旋同轴火箭喷射器中的液压损耗最小化最小化
6. Sustained Release from Injectable Composite Gels Loaded with Silver Nanowires Designed to Combat Bacterial Resistance in Bone Regeneration Applications [O] . Arianna De Mori, Meena Hafidh, Natalia Mele, 2019

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7. Establishment of Design Method for Liquid Hydrogen Regenerative Cooling Combustor of LOX/Hydrogen Rocket Engine [O] . Nobuyuki YATSUYANAGI 2009

机译：LOX /氢火箭发动机液氢再生冷却燃烧器设计方法的建立
8. High-Temperature Turbine-Technology Program. Phase II. Technology Test and Support Studies. Design and Development of a Regeneratively Fuel Cooled High Temperature Gas Turbine Combustor for Operation on Low Btu Gas [R] . Dobson, R. L., Kwan, T. C., Straume, T. 1982

机译：高温涡轮技术计划。第二阶段。技术测试和支持研究。低Btu气体下蓄热式高温燃气轮机燃烧器的设计与开发

Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector

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