小型溝構造液水冷却燃焼器の研究(II) (水冷却燃焼実験)

• Material Type: 文書・図像類
• Title: 小型溝構造液水冷却燃焼器の研究(II) (水冷却燃焼実験)
• 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: 1982-05
• Publication Date (W3CDTF): 1982-05
• Alternative Title: A Study on Heat Transfer Characteristics of Water Cooled LO2/LH2 Rocket Combustor
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-708
• No. or year of volume/issue: 708
• Volume: 708
• Pages: 35-
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Target Audience: 一般
• Note (General): Recently, new trends toward reusable high performance rocket engines have increased the demand for the knowledge to accurately predict the hot gas side heat transfer rate. While Bartz’s semi-empirical equation is usually recommended for predicting the heat transfer rate in the nozzle region, there is no established procedure for the chamber region, which plays an important role in predicting the amount of enthalpy increase of coolant in the regeneratively-cooled engines. With this motivation, an experimental investigation using the water-cooled calorimetric combustor was conducted to determine the local heat flux distribution along the axis and to study the boiling characteristics of cooling water under various combustion conditions. The inner contour of the combuster was the same as the one used in the authors’previous report“A Study of Liquid Hydrogen Cooled LO2/LH2 Rocket Combuster with Slotted Wall Liner”. The following results were noted: The variation of burning parameters, such as pressure, mixture ratio and hydrogen injection temperature, significantly influenced the distribution of wall heat flux rate along the axis and the total heat input to the wall. It was also shown, that the local value of heat transfer coefficient in the thrust chamber could be roughly correlated by the hydrogen-oxygen injection velocity ratio. In the coolant side, the surface with fine triangular fins was revealed to have excellent heat transfer characteristics. Three kinds of empirical formulas for the boiling characteristics on that surface, namely, the incipience of fully-developed nucleate boiling, heat transfer in nucleate boiling region and critical heat flux rate, were derived.; 資料番号: NALTR0708000; レポート番号: NAL TR-708
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44965&item_no=1&attribute_id=31&file_no=1
• 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