| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
Fabrication and Test of a Carbon-Carbon Composite Combustion Chamber for a Low Thrust Storable Engine |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
|
資源タイプ |
technical report |
| その他のタイトル |
|
|
その他のタイトル |
低推力貯蔵性推進薬エンジン用炭素複合材燃焼器の試作試験 |
| 著者 |
日下, 和夫
植田, 修一
阿部, 登
宮島, 博
桑原, 卓雄
小坂, 勝明
長島, 隆一
KUSAKA, Kazuo
UEDA, Shuichi
ABE, Noboru
MIYAJIMA, Hiroshi
KUWAHARA, Takuo
KOSAKA, Katsuaki
NAGASHIMA, Ryuichi
|
| 著者所属 |
|
|
|
航空宇宙技術研究所角田支所 |
| 著者所属 |
|
|
|
航空宇宙技術研究所角田支所 |
| 著者所属 |
|
|
|
航空宇宙技術研究所角田支所 |
| 著者所属 |
|
|
|
航空宇宙技術研究所角田支所 |
| 著者所属 |
|
|
|
日産自動車株式会社 |
| 著者所属 |
|
|
|
日産自動車株式会社 |
| 著者所属 |
|
|
|
宇宙開発事業団 |
| 著者所属（英） |
|
|
|
en |
|
|
Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
|
|
en |
|
|
Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
|
|
en |
|
|
Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
|
|
en |
|
|
Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
|
|
en |
|
|
Nissan Motor Co., Ltd. |
| 著者所属（英） |
|
|
|
en |
|
|
Nissan Motor Co., Ltd. |
| 著者所属（英） |
|
|
|
en |
|
|
National Space Development Agency of Japan(NASDA) |
| 出版者 |
|
|
出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
|
|
出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-946
巻 946,
p. 27,
発行日 1987-10
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
One possible approach to obtaining a high specific impulse in a low thrust bipropellant engine is to reduce the film cooling requirement by constructing a combustion chamber with a temperatrue resistant material yet-to-be-developed Carbon/Carbon (C/C) composite material is one such material whose high-temperature specific strength is very high. This report describes a preliminary effort to develop a C/C composite chamber, as well as to develop an injector for a low thrust storable engine. Performance tests of injectors for a 2000 N thrust class, fuel film cooled, NTO/MMH propellant engine were conducted at sea level with a workhorse combustion chamber. It was shown that a graphite nozzle insert could be used repeatedly for performance evaluation at a firing duration of 7 seconds. The energy release efficiencies of the core injectors used were estimated to be 97.5％ at the design mixture ratio of 1.65. The vacuum specific impulse predicted for an injector with 15％ film cooling with a 200:1 area ratio nozzle was 310s at a mixture ratio of 1.65 and a chamber pressure of 0.85 MPa. No combustion instability or popping were obserged up to a chamber presure of 1.6 MPa. A C/C composite chamber with SiC coating on the inner wall and organic silicide coating over the carbon CVD layer on the outer wall was selected for the firing test. Two sea level tests, of 30 s and 60 s durations, at a chamber pressure of 0.85 MPa were demonstrated on a single C/C composite chamber. It was shown that the basic C/C composite material had sufiicient high-temperature strength and that the SiC coating on the inner wall was durable at the operating conditions. The outside carbon CVD coating seemed to be effective in shutting off the permeability of the combustion gases from the inside of the chamber. However, the organic silicide coatings applied to protect the carbon CVD layer from oxidizing atmosphere in sea level tests were not sufficiently effective. The firing duration was limited to 60 s because of an inadequate seal between the C/C composite chamber and the metal injector. |
| ISSN |
|
|
収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0389-4010 |
| 資料番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR0946000 |
| レポート番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-946 |
naltr00946.pdf (3.7 MB)
