국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Application of C/C Composites to the Combustion Chamber of Rocket Engines Part 1 Heating Tests of C/C Composites with High Temperature Combustion Gases
저자	Makoto TADANO, Masahiro SATO, Yukio KURODA, Kazuo KUSAKA, Shuichi UEDA, Takeshi Suemitsu, Satoshi Hasegawa, Yukinori Kude
Keyword
URL	C/C composite; FGM coating; modified matrix coating
보고서번호	NAL TR-1264
발행년도	1995.4
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	To meet the lifespan requirement for thermal barrier coating,ceramic coating has been employed in eht hot-gas side wall.However,the main drawback to the use of C/C composite is the tendency for delamination to occur between the coating layer on the hot-gas side and the base materials on the cooling side during repeated thermal heating loads.To improve the thermal properties of the thermal barrier coating,five different types of 30-mm diameter C/C composite specimens constructed with Functionally Gradient Materials (FGMs) and a modified matrix coating layer were fabricated.In this test,these specimens were exposed to the combustion gases of the rocket engine using nitrogen tetroxide (NTO) / monomethyl hydrazine (MMH) to evaluate the properties of thermal and erosive resistance on the thermal barrier coating after the heating test.It was observed that modified matrix and coating with FGMs are effective in improving the thermal properties of C/C composite.