航天推进技术研究院主办
[1]张喆,金星,席文雄.基于逆向气体喷注的支板热防护研究[J].火箭推进,2018,44(05):48-55.
ZHANG Zhe,JIN Xing,XI Wenxiong.Research on thermal protection of strut based on reverse gas injection[J].Journal of Rocket Propulsion,2018,44(05):48-55.
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ZHANG Zhe,JIN Xing,XI Wenxiong.Research on thermal protection of strut based on reverse gas injection[J].Journal of Rocket Propulsion,2018,44(05):48-55.
基于逆向气体喷注的支板热防护研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年05期
页码:
48-55
栏目:
研究与设计
出版日期:
2018-10-31
- Title:
- Research on thermal protection of strut based on reverse gas injection
- 文章编号:
- 1672-9374(2018)05-0048-08
- Keywords:
- thermal environment; strut; reverse injection; thermal protection
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 超燃冲压发动机的支板在高飞行马赫数下工作时,面临着非常严峻的热环境。对飞行马赫数为8时的支板热环境进行了研究,得到了前缘钝化半径与支板表面温度的关系; 随后,对不同喷注总压,喷孔尺寸和喷注总温下的逆向喷注进行了数值模拟。数值模拟的结果表明,提高喷注总压和增大喷孔尺寸都有助于降低支板表面温度,在喷注总温上升到1 000 K时,逆向喷注仍然具有较好的热防护性能。
- Abstract:
- The strut of scramjet engine faces a severe thermal environment when operating at high Mach numbers.In this paper, the thermal environment of the strut was studied when the flight Mach number was 8 and the relationship between the passivation radius and the surface temperature of the strut was obtained.Subsequently, numerical simulations were carried out for the reverse injection under different injection total pressures, orifice sizes, and total injection temperatures.The results of numerical simulation show that increasing the total injection pressure and increasing the size of the orifice help to reduce the surface temperature of the strut.When the total injection temperature rises to 1 000 K, the reverse gas injection is still applicable.
参考文献/References:
[1] TOMIOKA S, MURAKAMI A, KUDO K, et al.Combustion tests of a staged supersonic combustor with a strut[J].Journal of propulsion & power, 2001, 17(2):293-300.
[2] BURNS R A.Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields[D].Texas: University of Texas at Austin,2014.
[3] 刘世杰.超燃冲压发动机支板流场RANS/LES模拟及燃烧过程试验研究[D].长沙:国防科学技术大学,2007.
[4] 苏义.支板超声速混合增强技术及其阻力特性研究[D].长沙:国防科学技术大学,2006.
[5] PIZZARELLI M, NASUTI F, ONOFRI M.Coupled wall heat conduction and coolant flow analysis for liquid rocket engines[J].Journal of propulsion & power, 2012, 29(1):34-41.
[6] ZHONG F Q, CHEN T Y, FAN X J, et al.Three-dimensional heat transfer analysis and optimized design of actively cooled strut for scramjet applications: AIAA2012-3926[R].Reston: AIAA,2012.
[7] 黄拯.高温与超音速条件下发汗冷却基础问题研究[D].北京:清华大学,2015.
[8] 熊宴斌.超声速主流条件发汗冷却的流动和传热机理研究[D].北京:清华大学,2013.
[9] 宁东坡.超声速燃烧室长时间工作稳燃支板性能研究[D].哈尔滨:哈尔滨工业大学,2015.
[10] 孙冰, 郑力铭.超燃冲压发动机支板热环境及热防护方案[J].航空动力学报, 2006, 21(2):336-341.
备注/Memo
收稿日期:2018-05-11
基金项目:国家自然科学基金(51606220)
作者简介: 张 喆(1993—),男,博士研究生,研究领域为等离子体流动控制
更新日期/Last Update:
1900-01-01