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)

Material type: 文書・図像類

Author: 新野, 正之ほか

Publisher: 航空宇宙技術研究所

Publication date: 1983-07

Material Format: Digital

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Note (General)：: 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...

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Material Type: 文書・図像類
Title: 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)
Author/Editor: 新野, 正之
熊川, 彰長
八柳, 信之
五味, 広美
鈴木, 昭夫
坂本, 博
佐々木, 正樹
柳川, 孝二
NIINO, Masayuki
KUMAKAWA, Akinaga
YATSUYANAGI, Nobuyuki
GOMI, Hiromi
SUZUKI, Akio
SAKAMOTO, Hiroshi
SASAKI, Masaki
YANAGAWA, Koji
Author Heading: 新野, 正之
熊川, 彰長
八柳, 信之
五味, 広美
鈴木, 昭夫
坂本, 博
佐々木, 正樹
柳川, 孝二
NIINO, Masayuki
KUMAKAWA, Akinaga
YATSUYANAGI, Nobuyuki
GOMI, Hiromi
SUZUKI, Akio
SAKAMOTO, Hiroshi
SASAKI, Masaki
YANAGAWA, Koji
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1983-07
Publication Date (W3CDTF): 1983-07
Alternative Title: A Study of Liquid Hydrogen Cooled LO2/LH2 Rocket Combustor with Channel Wall Construction
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-767
No. or year of volume/issue: 767
Volume: 767
Pages: 25-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): 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.
資料番号: NALTR0767000
レポート番号: NAL TR-767
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ