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Carbon fiber reinforced silicon carbide-hafnium carbide (C/SiC-HfC) composite was prepared by precursor infiltration and pyrolysis process. Then, ablation behavior of C/SiC-HfC was evaluated in plasma wind tunnel. It was found that oxide layer formed during ablation significantly influenced the surface temperature. Formation of dense HfO2-SiO2 layer under low heat flux led to stable surface temperature. Silica (SiO2) on the surface was gradually consumed when heat flux increased, resulting in conversion of HfO2-SiO2 on the surface to HfO2. Converted HfO2 with high catalytic coefficient absorbed more energy, causing gradual increase in the surface temperature. Formed oxide layer was destroyed at high heat flux and high stagnation point pressure. After carbon fiber lost the protection of HfO2-SiO2 layer, it burned immediately, leading to surface temperature jump.


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Ablation of C/SiC-HfC composite prepared by precursor infiltration and pyrolysis in plasma wind tunnel

Show Author's information Liuyang DUANaLei LUObLiping LIUa,cYiguang WANGd( )
Science and Technology on Thermostructural Composite Materials Laboratory, Northwestern Polytechnical University, Xi’an 710072, China
Beijing Institute of Long March Aerospace Vehicles, Beijing 100076, China
Ultrahigh Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Institute of Advanced Structure Technology, Beijing Institute of Technology, Haidian District, Beijing 100081, China

Abstract

Carbon fiber reinforced silicon carbide-hafnium carbide (C/SiC-HfC) composite was prepared by precursor infiltration and pyrolysis process. Then, ablation behavior of C/SiC-HfC was evaluated in plasma wind tunnel. It was found that oxide layer formed during ablation significantly influenced the surface temperature. Formation of dense HfO2-SiO2 layer under low heat flux led to stable surface temperature. Silica (SiO2) on the surface was gradually consumed when heat flux increased, resulting in conversion of HfO2-SiO2 on the surface to HfO2. Converted HfO2 with high catalytic coefficient absorbed more energy, causing gradual increase in the surface temperature. Formed oxide layer was destroyed at high heat flux and high stagnation point pressure. After carbon fiber lost the protection of HfO2-SiO2 layer, it burned immediately, leading to surface temperature jump.

Keywords:

C/SiC-HfC composite, precursor infiltration and pyrolysis, ablation, plasma wind tunnel
Received: 23 December 2019 Revised: 14 March 2020 Accepted: 31 March 2020 Published: 05 June 2020 Issue date: June 2020
References(45)
[1]
TH Squire, J Marschall. Material property requirements for analysis and design of UHTC components in hypersonic applications. J Eur Ceram Soc 2010, 30: 2239-2251.
[2]
DE Glass. Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles. In: Proceedings of the 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008: AIAA-2008-2682.
[3]
QS Ma, LH Cai. Fabrication and oxidation resistance of mullite/yttrium silicate multilayer coatings on C/SiC composites. J Adv Ceram 2017, 6: 360-367.
[4]
YD Xu, LT Zhang, LF Cheng, et al. Microstructure and mechanical properties of three-dimensional carbon/silicon carbide composites fabricated by chemical vapor infiltration. Carbon 1998, 36: 1051-1056.
[5]
W Krenkel, F Berndt. C/C-SiC composites for space applications and advanced friction systems. Mat Sci Eng A 2005, 412: 177-181.
[6]
I Sakraker, CO Asma. Experimental investigation of passive/active oxidation behavior of SiC based ceramic thermal protection materials exposed to high enthalpy plasma. J Eur Ceram Soc 2013, 33: 351-359.
[7]
MJH Balat. Determination of the active-to-passive transition in the oxidation of silicon carbide in standard and microwave-excited air. J Eur Ceram Soc 1996, 16: 55-62.
[8]
WL Vaughn, HG Maahs. Active-to-passive transition in the oxidation of silicon carbide and silicon nitride in air. J Am Ceram Soc 1990, 73: 1540-1543.
[9]
MM Opeka, IG Talmy, JA Zaykoski. Oxidation-based materials selection for 2000 °C + hypersonic aerosurfaces: Theoretical considerations and historical experience. J Mater Sci 2004, 39: 5887-5904.
[10]
Y Arai, R Inoue, K Goto, et al. Carbon fiber reinforced ultra-high temperature ceramic matrix composites: A review. Ceram Int 2019, 45: 14481-14489.
[11]
X Zhao, YG Wang, LY Duan, et al. Improved ablation resistance of C/SiC-ZrB2 composites via polymer precursor impregnation and pyrolysis. Ceram Int 2017, 43: 12480-12489.
[12]
KX Gui, FY Liu, G Wang, et al. Microstructural evolution and performance of carbon fiber-toughened ZrB2 ceramics with SiC or ZrSi2 additive. J Adv Ceram 2018, 7: 343-351.
[13]
ZJ Yu, X Lv, SY Lai, et al. ZrC-ZrB2-SiC ceramic nanocomposites derived from a novel single-source precursor with high ceramic yield. J Adv Ceram 2019, 8: 112-120.
[14]
YT Chen, W Sun, X Xiong, et al. Microstructure, thermophysical properties, and ablation resistance of C/HfC-ZrC-SiC composites. Ceram Int 2019, 45: 4685-4691.
[15]
J Chen, YG Wang, LF Cheng, et al. Thermal diffusivity of three-dimensional needled C/SiC-TaC composites. Ceram Int 2011, 37: 3095-3099.
[16]
QB Wen, R Riedel, E Ionescu. Solid-solution effects on the high-temperature oxidation behavior of polymer-derived (Hf, Ta)C/SiC and (Hf, Ti)C/SiC ceramic nanocomposites. Adv Eng Mater 2019, 21: 1800879.
[17]
JP Zhang, JL Qu, QG Fu. Ablation behavior of nose-shaped HfB2-SiC modified carbon/carbon composites exposed to oxyacetylene torch. Corros Sci 2019, 151: 87-96.
[18]
SQ Guo, K Naito, Y Kagawa. Mechanical and physical behaviors of short pitch-based carbon fiber-reinforced HfB2-SiC matrix composites. Ceram Int 2013, 39: 1567-1574.
[19]
YT Chen, W Sun, X Xiong, et al. Microstructure, thermophysical properties, and ablation resistance of C/HfC-ZrC-SiC composites. Ceram Int 2019, 45: 4685-4691.
[20]
L Luo, YG Wang, LY Duan, et al. Ablation behavior of C/SiC-HfC composites in the plasma wind tunnel. J Eur Ceram Soc 2016, 36: 3801-3807.
[21]
VC Agte, H Altertum. Untersuchungen über systeme hochschmelzender carbide nebst beitr ägen zum problem der kohlenstoffschmelzung. Z Tech Physik 1930, 11: 182.
[22]
SM Lakiza, JS Tyschenko, LM Lopato. Phase diagram of the Al2O3-HfO2-Y2O3 system. J Eur Ceram Soc 2011, 31: 1285-1291.
[23]
D Huang, MY Zhang, QZ Huang, et al. Mechanical property, oxidation and ablation resistance of C/C-ZrB2- ZrC-SiC composite fabricated by polymer infiltration and pyrolysis with preform of Cf/ZrB2. J Mater Sci Technol 2017, 33: 481-486.
[24]
CL Yan, RJ Liu, CR Zhang, et al. Ablation and mechanical properties of 3D braided C/ZrC-SiC composites with various SiC/ZrC ratios. Ceram Int 2016, 42: 19019-19026.
[25]
LY Duan, X Zhao, YG Wang. Comparative ablation behaviors of C/SiC-HfC composites prepared by reactive melt infiltration and precursor infiltration and pyrolysis routes. Ceram Int 2017, 43: 16114-16120.
[26]
HB Fan, NK Ravala, HC Wikle III, et al. HfC structural foams synthesizing from polymer precursors. In: Innovative Processing and Synthesis of Ceramics, Glasses and Composites IX. NP Singh, BG Bansal, T Nair, et al. Eds. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2012: 13-24.
[27]
QB Wen, XG Luan, L Wang, et al. Laser ablation behavior of SiHfC-based ceramics prepared from a single-source precursor: Effects of Hf-incorporation into SiC. J Eur Ceram Soc 2019, 39: 2018-2027.
[28]
DVN Harish, A Bharatish, HNN Murthy, et al. Evaluation of nanosecond laser ablation and scratch resistance of tantalum carbide coated graphite substrates. Ceram Int 2019, 45: 22578-22588.
[29]
A Nisar, S Ariharan, T Venkateswaran, et al. Effect of carbon nanotube on processing, microstructural, mechanical and ablation behavior of ZrB2-20SiC based ultra-high temperature ceramic composites. Carbon 2017, 111: 269-282.
[30]
S Mungiguerra, GD di Martino, A Cecere, et al. Arc-jet wind tunnel characterization of ultra-high-temperature ceramic matrix composites. Corros Sci 2019, 149: 18-28.
[31]
F Panerai, B Helber, O Chazot, et al. Surface temperature jump beyond active oxidation of carbon/silicon carbide composites in extreme aerothermal conditions. Carbon 2014, 71: 102-119.
[32]
M Auweter-Kurtz, HL Kurtz, S Laure. Plasma generators for re-entry simulation. J Propul Power 1996, 12: 1053-1061.
[33]
F Monteverde, R Savino, M de Stefano Fumo, et al. Plasma wind tunnel testing of ultra-high temperature ZrB2-SiC composites under hypersonic re-entry conditions. J Eur Ceram Soc 2010, 30: 2313-2321.
[34]
F Monteverde, R Savino, M de Stefano Fumo. Dynamic oxidation of ultra-high temperature ZrB2-SiC under high enthalpy supersonic flows. Corros Sci 2011, 53: 922-929.
[35]
P Lespade, N Richet, P Goursat. Oxidation resistance of HfB2-SiC composites for protection of carbon-based materials. Acta Astronaut 2007, 60: 858-864.
[36]
YG Wang, BS Ma, LL Li, et al. Oxidation behavior of ZrB2-SiC-TaC ceramics. J Am Ceram Soc 2012, 95: 374-378.
[37]
L Luo, YG Wang, LP Liu, et al. Ablation behavior of C/SiC composites in plasma wind tunnel. Carbon 2016, 103: 73-83.
[38]
T Grau, E Messerschmid. Numerical investigation of a partially ionized air flow in a plasma wind tunnel. In: Proceedings of the 7th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 1998: AIAA-98-2955.
[39]
D Alfano, L Scatteia, S Cantoni, et al. Emissivity and catalycity measurements on SiC-coated carbon fibre reinforced silicon carbide composite. J Eur Ceram Soc 2009, 29: 2045-2051.
[40]
GR Holcomb. Countercurrent gaseous diffusion model of oxidation through a porous coating. Corrosion 1996, 52: 531-539.
[41]
F Yang, JM Gu, LH Ye, et al. Justifying the significance of Knudsen diffusion in solid oxide fuel cells. Energy 2016, 95: 242-246.
[42]
R Savino, M de Stefano Fumo, L Silvestroni, et al. Arc-jet testing on HfB2 and HfC-based ultra-high temperature ceramic materials. J Eur Ceram Soc 2008, 28: 1899-1907.
[43]
S Caniglia, GL Barna. Handbook of Industrial Refractories Technology: Principles, Types, Properties and Applications. William Andrew, 1992: 135.
[44]
B Helber, O Chazot, A Hubin, et al. Microstructure and gas-surface interaction studies of a low-density carbon-bonded carbon fiber composite in atmospheric entry plasmas. Compos Part A: Appl S 2015, 72: 96-107.
[45]
M Gasch, D Ellerby, E Irby, et al. Processing, properties and arc jet oxidation of hafnium diboride/silicon carbide ultra high temperature ceramics. J Mater Sci 2004, 39: 5925-5937.
Publication history
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Acknowledgements
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Publication history

Received: 23 December 2019
Revised: 14 March 2020
Accepted: 31 March 2020
Published: 05 June 2020
Issue date: June 2020

Copyright

© The Author(s) 2020

Acknowledgements

The authors greatly acknowledge the financial support from the National Natural Science Foundation of China (Grant No. 51972027).

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