Ablative Mechanism of SiC Coated Carbon/carbon Composites with Ratio of Oxygen to Fuel at Combusion Test

연소시험에서 산소와 연료 비에 따른 탄화규소로 코팅된 탄소/ 탄소 복합재의 삭마 메커니즘

  • Zhang, Eun-Hee (Resin Application Team, Kumho Petrochemical R&BD Center) ;
  • Kim, Zeong-Baek (Department of Polymer Science and Engineering, Chungnam National University) ;
  • Joo, Hyeok-Jong (Department of Polymer Science and Engineering, Chungnam National University)
  • 장은희 (금호석유화학 중앙연구소) ;
  • 김정백 (충남대학교 고분자공학과) ;
  • 주혁종 (충남대학교 고분자공학과)
  • Received : 2007.01.29
  • Accepted : 2007.05.03
  • Published : 2007.06.10

Abstract

Carbon/carbon (C/C) composites as unique materials possess exceptional thermal resistance with light weight, high stiffness, and strength even at high temperature. However, one serious obstacle for application of the C/C composites is their poor oxidation resistance in high temperature oxidizing environments. SiC coating has been employed to protect the composites from oxidation. This study explored combustion characteristics of 4-directional (4D) carbon/carbon composites using liquid fuel rocket engine to investigate ablative motion of the materials. C/C composites were made of coal tar pitch as a matrix precursor, and heat-treated at $2300^{\circ}C$. Throughout repeated densification process, the density of the material reached $1.903g/cm^3$. After machining 4D C/C composites, the nozzle surface was coated by a SiC layer by pack-cementation method to improve oxidation resistance. Erosion characteristics of SiC-coated C/C composites were measured as function of the ratio of oxygen to fuel. The morphological change of the composites after combustion test was investigated using SEM and erosion mechanism also was discussed.

Keywords

carbon/carbon composites;SiC coating;ablative behavior;combustion test;rocket motor nozzle

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