航天推进技术研究院主办
[1]孔维鹏,王天泰,谢 恒,等.气氢/液氧同轴喷注器变工况燃烧流场相似性[J].火箭推进,2023,49(02):27-34.
KONG Weipeng,WANG Tiantai,XIE Heng,et al.Similarity of combustion flow field in LOX/GH2 coaxial injector under variable operating conditions[J].Journal of Rocket Propulsion,2023,49(02):27-34.
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KONG Weipeng,WANG Tiantai,XIE Heng,et al.Similarity of combustion flow field in LOX/GH2 coaxial injector under variable operating conditions[J].Journal of Rocket Propulsion,2023,49(02):27-34.
气氢/液氧同轴喷注器变工况燃烧流场相似性
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年02期
页码:
27-34
栏目:
目次
出版日期:
2023-04-25
- Title:
- Similarity of combustion flow field in LOX/GH2 coaxial injector under variable operating conditions
- 文章编号:
- 1672-9374(2023)02-0027-08
- Keywords:
- hydrogen-oxygen expansion cycle rocket engine; coaxial shear injector; combustion flow field; similarity; variable operating condition; scale technology
- 分类号:
- V434.1
- 文献标志码:
- A
- 摘要:
- 为研究不同室压工况下气氢/液氧燃烧流场的相似性,设计了喷注器试验件,并采用数值仿真和热试验的方法对气氢/液氧喷注器的喷雾燃烧流场进行了研究。数值仿真选取试验件的1/6进行三维稳态计算,其中湍流模型采用SST k-ω模型、化学反应采用考虑氢氧6组分9步反应机理的涡耗散概念模型、液氧液滴采用离散相模型,共进行了2.8～9.8 MPa范围内8种典型工况的数值仿真。热试验采用气氢/液氧推进剂,进行了4.5 MPa、5.4 MPa和6.8 MPa这3种不同室压工况共4次挤压热试验,采用量热式水冷身部对燃烧室壁面热流进行了测量。仿真和试验结果表明:对于气氢/液氧同轴直流喷注器,在混合比、氢氧温度和喷注速度相同的情况下,当室压大于液氧临界压力时的燃烧流场具有相似性; 而室压小于液氧临界压力时的燃烧流场与大于临界压力的燃烧流场结构存在差异。
- Abstract:
- In order to study the similarity of LOX/GH2 combustion flow field under different chamber pressure, the injector test article was designed, and the spray combustion flow field of LOX/GH2 injector was studied by numerical simulation and hot-fire test.In the numerical simulation, one sixth of the test article was selected for 3D steady state calculation. The turbulence model was based on the SST k-ω model, and the eddy dissipation concept model with chemical reaction mechanism of 9 steps for 6 components was used in the chemical reaction.In addition, the discrete phase model was adopted for the liquid oxygen droplet.A total of 8 typical working conditions were simulated in the range of 2.8-9.8 MPa.In the hot-fire test, LOX/GH2 was used as propellants, and four extrusion heat tests were carried out under three different chamber pressure conditions of 4.5 MPa, 5.4 MPa and 6.8 MPa.The wall heat flux of the combustion chamber was measured by the calorimetric water-cooled body.The simulation and test results show that in the case of the same mixing ratio, temperature and injection speed, the combustion flow field of LOX/GH2 coaxial shear injector is similar under the supercritical pressure of liquid oxygen.While the structure of the combustion flow field is different under the subcritical and supercritical pressure.
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备注/Memo
收稿日期:2022-01-02; 修回日期:2022-03-31
基金项目:装备预研航天科技联合基金(6141B061207)
作者简介:孔维鹏(1992—),男,博士,工程师,研究领域为液体火箭发动机推力室设计。
更新日期/Last Update:
1900-01-01