Combustion Characteristics of Oxygen/Hydrogen High Pressure Preburners for Staged Combustion Cycle Rocket Engine

Material type: 文書・図像類

Author: 小野, 文衛ほか

Publisher: 航空宇宙技術研究所

Publication date: 1989-11

Material Format: Digital

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Note (General)：: The influence of preburner design and operating conditions on the combustion characteristics of high pressure fuel rich preburners with oxygen/hydroge...

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Material Type: 文書・図像類
Title: Combustion Characteristics of Oxygen/Hydrogen High Pressure Preburners for Staged Combustion Cycle Rocket Engine
Author/Editor: 小野, 文衛
田村, 洋
坂本, 博
佐々木, 正樹
ONO, Fumiei
TAMURA, Hiroshi
SAKAMOTO, Hiroshi
SASAKI, Masaki
Author Heading: 小野, 文衛
田村, 洋
坂本, 博
佐々木, 正樹
ONO, Fumiei
TAMURA, Hiroshi
SAKAMOTO, Hiroshi
SASAKI, Masaki
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1989-11
Publication Date (W3CDTF): 1989-11
Alternative Title: 酸素-水素・高圧プリバーナの燃焼特性
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1044
No. or year of volume/issue: 1044
Volume: 1044
Pages: 27-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): The influence of preburner design and operating conditions on the combustion characteristics of high pressure fuel rich preburners with oxygen/hydrogen propellant was experimentally evaluated using small scale hardware. Seven different types of preburners whose injectors consisted of one to six coaxial type injection elements were tested. Gaseous oxygen at room temperature and liquid oxygen were used as oxidizer, and gaseous hydrogen at room temperature and such hydrogen at low(83-117K) were used as fuel. Testing also covered a combustion pressure range of 5.0 to 15.1 MPa, an oxidizer to fuel ratio range from 0.22 to 0.83 and an injection element propellant flow rate range from 0.026 to 0.238 kg/sec. Combustion performance and gas temperature uniformity data are presented for each preburner. Measured combustion performances were nearly 100％ for all preburners over the tested range. Measured temperature uniformity was correlated by an empirical correlation parameter which accounts for the effects of oxidizer to fuel ratio, shear force due to oxygen and hydrogen injection velocity difference, and combustion gas residence time. Abnormal combustion phenomena which were characterized by abnormally low combustion performance and low combustion gas temperature were observed. The phenomena were interpreted as meaning that the propellant injected from some coaxial elements did not burn due to misignition.
資料番号: NALTR1044000
レポート番号: NAL TR-1044
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45303&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45303&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