留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

半潜入喷管收敛段碳/酚醛材料烧蚀特性

巩伦昆 邓哲 魏晓林

巩伦昆, 邓哲, 魏晓林. 半潜入喷管收敛段碳/酚醛材料烧蚀特性[J]. 航空动力学报, 2021, 36(11): 2379-2388. doi: 10.13224/j.cnki.jasp.20200413
引用本文: 巩伦昆, 邓哲, 魏晓林. 半潜入喷管收敛段碳/酚醛材料烧蚀特性[J]. 航空动力学报, 2021, 36(11): 2379-2388. doi: 10.13224/j.cnki.jasp.20200413
GONG Lunkun, DENG Zhe, WEI Xiaolin. Ablation characteristics of carbon/phenolic at converging section in semi-submerged nozzle[J]. Journal of Aerospace Power, 2021, 36(11): 2379-2388. doi: 10.13224/j.cnki.jasp.20200413
Citation: GONG Lunkun, DENG Zhe, WEI Xiaolin. Ablation characteristics of carbon/phenolic at converging section in semi-submerged nozzle[J]. Journal of Aerospace Power, 2021, 36(11): 2379-2388. doi: 10.13224/j.cnki.jasp.20200413

半潜入喷管收敛段碳/酚醛材料烧蚀特性

doi: 10.13224/j.cnki.jasp.20200413
详细信息
    作者简介:

    巩伦昆(1989-),男,助理研究员,博士,研究方向为火箭发动机设计。

  • 中图分类号: V235

Ablation characteristics of carbon/phenolic at converging section in semi-submerged nozzle

  • 摘要: 采用流固热耦合数值方法,以及Abaqus的ALE(arbitrary Lagrangian-Eulerian,任意拉格朗日欧拉方法)自适应网格技术,对位于半潜入喷管收敛段的碳/酚醛的烧蚀现象进行了预估,与试验结果进行了对比分析。结果表明:在收敛段,Al/Al2O3液滴或颗粒对材料的传热烧蚀起到了关键作用,当气流与材料表面平行时,液滴或颗粒的影响很小;从碳/酚醛热分解角度出发,基于完全碳化即被剥蚀的假设,基本能够预估碳/酚醛材料的烧蚀特征,烧蚀速率大约为0.3 mm/s;后效碳化对材料碳化过程的影响明显,发动机工作期间,分解层的厚度大约为2.0 mm,考虑后效作用,分解层厚度可能会增加至4.0 mm左右;与喉衬接触的材料区域,喉衬的传热会明显加剧材料的碳化过程。

     

  • [1] 郑雷,蔡峨,冯文澜.碳酚醛材料的温度场及烧蚀研究[J].推进技术,1990,1:14-19.
    [2] BIANCHI D,TURCHI A,NASUTI F,et al.Chemical erosion of carbon-phenolic rocket nozzles with finite-rate surface chemistry[J].Journal of Propulsion and Power,2013,29(5):1220-1230.
    [3] CROSS P G,BOYD I D.Two-dimensional modeling of ablation and pyrolysis with application to rocket nozzles[J].Journal of Propulsion and Power,2017,54(1):212-224.
    [4] CROSS P G.Coupled simulations of finite-rate ablation with pyrolysis in rocket nozzles[J].Journal of Thermophysics and Heat Transfer,2020,34(2):381-392.
    [5] CHENG G C,VENKATACHARI B S,COZMUTA I.Multi-scale simulations of in-depth pyrolysis of charring ablative thermal protection material[J].Computers and Fluids,2011,45:191-196.
    [6] 张拜.防热材料烧蚀行为和热响应的数值仿真研究[D].兰州:兰州理工大学,2019.
    [7] 张运法.低密度碳/酚醛复合材料高温响应数值模拟分析[D].哈尔滨:哈尔滨工业大学,2019.
    [8] 王潇敏.树脂基热防护材料烧蚀传热机理及参数分析[D].合肥:中国科学技术大学,2018.
    [9] LI Weijie,HUANG Haiming,WANG Qing,et al.Protection of pyrolysis gases combustion against charring materials surface ablation[J].International Journal of Heat and Mass Transfer,2016,102:10-17.
    [10] NEILSON J H,GILCHRIST A.Erosion by a stream of solid particles[J].Wear,1968,11(2):111-122.
    [11] NEILSON J H,GILCHRIST A.An experimental investigation into aspects of erosion in rocket motor nozzles[J].Wear,1968,11(2):123-143.
    [12] OKA Y I,OKAMURA K,YOSHIDA T.Practical estimation of erosion damage caused by solid particle impact:Part 1 effects of impact parameters on a predictive equation[J].Wear,2005,259(1/2/3/4/5/6):95-101.
    [13] OKA Y I,YOSHIDA T.Practical estimation of erosion damage caused by solid particle impact:Part 2 mechanical properties of materials directly associated with erosion damage[J].Wear,2005,259(1/2/3/4/5/6):102-109.
    [14] THAKRE P,RAWAT R,CLAYTON R.Mechanical erosion of graphite nozzle in solid-propellant rocket motor[J].Journal of Propulsion and Power,2013,29(3):593-602.
    [15] GEISLER R L.A global view of the use of aluminum fuel in solid rocket motors[J].AIAA-2002-3748,2002.
    [16] 邓为.固体火箭发动机喷管内粒子侵蚀数值研究[D].哈尔滨:哈尔滨工程大学,2017.
    [17] 常桁,刘一白,刘宇,等.固体火箭发动机碳基材料喷管机械侵蚀特性[J].航空动力学报,2016,31(3):756-762.
    [18] YANG B C,CHEUNG F B.Numerical investigation of thermo-chemical and mechanical erosion of ablative materials[R].AIAA-93-2045,1993.
    [19] YANG B C,CHEUNG F B,KOO J H.Prediction of thermo-mechanical erosion of high-temperature ablatives in the SSRM Facility[R].AIAA-95-0254,1995.
    [20] POTTS R L.Hybrid integral/quasi-steady solution of charring abaltion[J].AIAA-90-1677,1990.
    [21] 鲍福廷,侯晓.固体火箭发动机设计[M].北京:中国宇航出版社,2016.
  • 加载中
计量
  • 文章访问数:  346
  • HTML浏览量:  140
  • PDF量:  101
  • 被引次数: 0
出版历程
  • 收稿日期:  2020-09-30
  • 刊出日期:  2021-11-28

目录

    /

    返回文章
    返回