Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
National Space Development Agency of Japan(NASDA)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-767
巻
767
ページ
25
発行年
1983-07
抄録（英）
This is the final report on “A Study of Liquid Hydrogen Cooled LO2/LH2 Rocket Combustor”which has been conducted as a NAL-NASDA joint research program since 1977. Heretofore, an experimental investigation was conducted to determine the cooling characteristics of LH2 and combustion efficiency characteristics by using a sub-sized combustor with channel wall construction. In this report thermo-hydraulic behavior of the coolant in the channels of the combustor was investigated by using an improved combustor. The following conclusions are based on studies of two combustors. 1)Liquid hydrogen heat transfer correlations including the asymmetric heating effects were derived. These empirical equtions were able to predict over 95％ of all the present experimental data within ±20％ errors. 2)The correlation for the characteristic velocity efficiency was empirically derived. The equation succeeded in correlating all data within ±2％ errors. To verify the usefulness of these results, the relationships between the present subsized combustors and the full-sized“LE-5”engine, were discussed.
小型溝構造液水冷却燃焼器の研究(第3報)(大型燃焼器との関連性)
naltr00767.pdf
(1.76MB)
