液酸・液水ロケットエンジン用点火器の真空着火試験

Material type: 文書・図像類

Author: 木皿, 且人ほか

Publisher: 航空宇宙技術研究所

Publication date: 1982-08

Material Format: Digital

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Note (General)：: The LE-5 engine, which will be installed in the second stage of Japan’s next launch vehicle, requires tank head ignition of the main thrust chamber an...

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Material Type: 文書・図像類
Title: 液酸・液水ロケットエンジン用点火器の真空着火試験
Author/Editor: 木皿, 且人
宮島, 博
阿部, 登
佐藤, 政裕
鎌田, 真
須藤, 孝幸
毛呂, 明夫
鳥井, 義弘
KISARA, Katsuto
MIYAJIMA, Hiroshi
ABE, Noboru
SATO, Masahiro
KAMATA, Makoto
SUDO, Takayuki
MORO, Akio
TORII, Yoshihiro
Author Heading: 木皿, 且人
宮島, 博
阿部, 登
佐藤, 政裕
鎌田, 真
須藤, 孝幸
毛呂, 明夫
鳥井, 義弘
KISARA, Katsuto
MIYAJIMA, Hiroshi
ABE, Noboru
SATO, Masahiro
KAMATA, Makoto
SUDO, Takayuki
MORO, Akio
TORII, Yoshihiro
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1982-08
Publication Date (W3CDTF): 1982-08
Alternative Title: VACUUM IGNITION TESTS OF IGNITERS FOR AN OXYGEN/HYDROGEN ROCKET ENGINE
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-732
No. or year of volume/issue: 732
Volume: 732
Pages: 22-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): The LE-5 engine, which will be installed in the second stage of Japan’s next launch vehicle, requires tank head ignition of the main thrust chamber and allows a small pressure budget to the igniter. Vacuum ignition tests of the original igniter revealed that its ignitability was marginal to the requirement. This experimental study was conducted to obtain information to improve the vacuum ignitability of the air-gap type torch igniter. Vacuum ignition tests of the modified igniters as well as the original igniter were conducted to obtain the minimum ignition pressure as a function of mixture ratio, i.e., lines of demarcation between the ignition and no-ignition regions in the preignition chamber pressure-mixture ratio plane. For the film cooled igniter, a marked reduction of the minimum ignition pressure was demonstrated by the combined effect of the following modifications:(1)locate the igniter throat just downstream of the film coolant injection ports, (2)reduce the throat diameter to half that of the original igniter, and (3)make 6 spikes on the otherwise circular cross section of the cathode, the spikes being in line with 6 fuel orifices. Of the above three modifications, the reduction of the throat diameter were shown to be the most effective in improving the vacuum ignitability. The minimun ignition pressure for different throat diameters was correlated well by the Reynolds number of oxygen flowing the annular cross section of the spark gap. Test results of a dump cooled igniter, photographic observations of the electric discharge over the annular gap, a discussion of the possible mechanism of a ignition failure, and the effect of an inadvertent solid particle contamination on the ignitability are also described.
資料番号: NALTR0732000
レポート番号: NAL TR-732
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