富氢/富氧燃气同轴双剪切气-气喷嘴性能仿真分析

姜金朋; 金平; 蔡国飙; 王珏

富氢/富氧燃气同轴双剪切气-气喷嘴性能仿真分析

1.
北京航空航天大学宇航学院, 北京 100191
2.
中国运载火箭技术研究院总体设计部, 北京 100076

基金项目: 国家高技术研究发展计划

计量
- 文章访问数: 1780
- HTML浏览量: 127
- PDF量: 902
- 被引次数: 0
出版历程
- 收稿日期: 2012-06-20
- 刊出日期: 2013-06-28

Orthogonal optimization design for a hydrogen-rich/oxygen-rich shear tricoaxial gas-gas injector

1.
School of Astronautics, Beijing University of Aeronautics Astronautics, Beijing 100191, China
2.
Systems Engineering Division, China Academy of Launch Vehicle Technology, Beijing 100076, China

摘要

摘要: 为研究富氢/富氧燃气同轴双剪切气-气喷嘴设计参数对燃烧性能和燃烧室热载的影响,采用正交试验设计方法对这些参数进行组合,数值模拟单喷嘴燃烧室流场,并以燃烧长度、燃烧室壁面和喷注面板处平均燃气温度为指标评价燃烧性能和热载.结果表明:燃氧速度比对燃烧性能和燃烧室热载影响最显著,中心氢流量比例对燃烧室热载影响非常显著,氧压降比对喷注面板处燃气平均温度的影响也很显著,而喷嘴出口壁厚对喷嘴性能影响不明显.燃氧速度比和氧压降比的交互作用对喷嘴性能有一定影响,而其他设计参数之间的交互作用对喷嘴性能影响非常小.最短燃烧室长度为117.9mm,最低壁面燃气温度及面板燃气温度分别为1637.7K和806.6K.
- 同轴双剪切气-气喷嘴 /
- 喷嘴设计参数 /
- 数值仿真 /
- 正交试验设计 /
- 燃烧性能 /
- 燃烧室热载
Abstract: To study the influence of the design parameters of a hydrogen-rich/oxygen-rich shear tricoaxial gas-gas injector on the combustion performance and the heat load performance, the parameters were fitted combination through the orthogonal experiment design method. The flow field of the single injector combustor was simulated. Evaluation indexes were the combustion length, the average gas temperature on combustion chamber wall and the average gas temperature on the injection faceplate. The results show that the fuel velocity to the oxidizer velocity has the most remarkable influence on the combustion performance and the heat load performance, the percentage of the central fuel mass flow rate has very obvious impact on the heat load performance, and the ratio of the oxidizer pressure drop to the combustor pressure has notable influence on the faceplate temperature, while the oxidizer post tip wall thickness has insignificant influence on the performance of the injector. To some extent, the interaction between the velocity ratio and oxidizer pressure drop affects the performance of the injector, while other interactions of the design parameters have little influence. The shortest combustion length i s 117.9mm. The lowest wall temperature is 1637.7K, and faceplate temperature is 806.6K.
- shear tricoaxial gas-gas injector /
- injector design parameters /
- numerical simulation /
- orthogonal experiment /
- combustion performance /
- combustion chamber heat load

HTML

参考文献(16)

[1]	金平,杜正刚,杨立军,等.气-气喷注器混合场流动显示[J].航空动力学报,2011,26(1):210-216. JIN Ping,DU Zhenggang,YANG Lijun,et al.Flow visualization of gas-gas injector mixing flowfield[J].Journal of Aerospace Power,2011,26(1):210-216.(in Chinese)
[2]	Davis J A,Campbell R L.Advantages of a full-flow staged combustion cycle engine system[R].AIAA 97-3318,1997.
[3]	Tucker P K,Klem M D,Smith T D,et al.Design of efficient GO₂/GH₂ injectors:a NASA,industry and university cooperative effort[R].AIAA 97-3350,1997.
[4]	Farhangi S,Yu T,Rojas L,et al.Gas-gas injector technology for full flow stage combustion cycle application[R].AIAA 99-2757,1999.
[5]	Vaidyanathan A,Gustavsson J,Segal C.One-and three-dimensional wall heat flux calculations in a O₂/H₂ system[J].Journal of Propulsion and Power,2010,26(1):186-189.
[6]	Vaidyanathan A,Gustavsson J,Segal C.Oxygen/hydrogen-planar-laser-induced fluorescence measurements and accuracy investigation in high-pressure combustion[J].Journal of Propulsion and Power,2009,25(4):864-874.
[7]	Shyy W,Tucker P K,Vaidyanathan R.Response surface and neural network techniques for rocket engine injector optimization[J].Journal of Propulsion and Power,2001,17(2):391-401.
[8]	Vaidyanathan R,Tucker P K,Papila N,et al.Computational-fluid-dynamics-based design optimization for single-element rocket injector[J].Journal of Propulsion and Power,2004,20(4):705-717.
[9]	Conley A,Vaidyanathan A,Segal C.Heat flux measurements for a GO₂/GH₂ single-element,shear injector[J].Journal of Spacecraft and Rockets,2007,44(3):633-639.
[10]	李茂,高玉闪,金平,等.气气喷嘴推进剂入口温度对燃烧和壁温的影响[J].北京航空航天大学学报,2011,37(9):1091-1094. LI Mao,GAO Yushan,JIN Ping,et al.Effects of propellants temperature in gas-gas injector inlet on combustion performance and wall temperature[J].Journal of Beijing University of Aeronautics and Astronautics,2011,37(9):1091-1094.(in Chinese)
[11]	Berque J,Sion M,Thomas J L.Tricoaxial injector technology development[J].AIAA-99-2492,1999.
[12]	Fournet A,Lonchard J M,Thomas J L.Technological demonstration for low cost gas generator[J].AIAA 2004-4006,2004.
[13]	Cai G,Wang X,Jin P,et al.Experimental and numerical investigation of large mass flow rate gas-gas injectors[R].AIAA 2008-4652,2008.
[14]	Du Z,Gao Y,Li M,et al.Numerical simulation of dual shear coaxial gas-gas injector[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(6):683-686.
[15]	Du Z,Li M,Jin P,et al.Large mass flow rate gas-gas injector optimization design with response surface methodology[J].Journal of Beijing University of Aeronautics and Astronautics,2010,36(4):395-398.
[16]	李茂,金平,蔡国飙.富氢/富氧燃气同轴剪切气-气喷嘴性能仿真分析[J].航空动力学报,2010,25(12):2827-2833. LI Mao,JIN Ping,CAI Guobiao.Performance simulation analysis for a hydrogen-rich/oxygen-rich shear coaxial gas-gas injector[J].Journal of Aerospace Power,2010,25(12):2827-2833.(in Chinese).