JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
63150000.pdf5.83 MB
title高温高圧燃焼試験設備の拡充整備
Other TitleHigh-temperature & high-pressure combustion test facility in JAXA
Author(jpn)下平 一雄; 山田 秀志; 牧野 敦; 山本 武; 林 茂
Author(eng)Shimodaira, Kazuo; Yamada, Hideshi; Makino, Atsushi; Yamamoto, Takeshi; Hayashi, Shigeru
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 航空プログラムグループ; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 航空プログラムグループ; 宇宙航空研究開発機構 航空プログラムグループ
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Aerospace Technology; Japan Aerospace Exploration Agency Aviation Program Group; Japan Aerospace Exploration Agency Institute of Aerospace Technology; Japan Aerospace Exploration Agency Aviation Program Group; Japan Aerospace Exploration Agency Aviation Program Group
Issue Date2006-03-31
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2006-03-31
Languagejpn
AbstractJAXA AP-7 High-Temperature & High-Pressure Combustion Test Facility is a unique facility that can supply air at temperatures up to 1,000 K and pressures up to 5 MPa. In order to make this facility more attractive and useful in developing combustors of aero-engines, every effort has been made to increase flow rates of air up to 4.0 kg/s, which is the triple of the previous performance. A traversing measurement system and a direct monitoring system for combustion are also equipped in this facility. By virtue of the augmentation of airflow rate, we can meet the requirement, up to about 2 MPa, for conducting combustion tests of sector combustors, to be installed in the ECO engine, being aimed for production in the 'Research and Development for an Environment-Friendly, Small Aircraft Engine' project, supervised by the Ministry of Economy, Trade and Industry. Furthermore, this augmentation gives us an opportunity for developing a low-NOx fuel-injector for the single combustor of the next generation civil aero-engines, operating under high-pressure ratios. Having finished competitive combustion tests for examining performance of sector combustions for ECO engines, it is strongly anticipated for this facility to be used in refining the combustor, to be selected in the competition.
高温高圧燃焼試験設備の拡充整備が完了した。これにより、圧力5MPa、温度1,000K、流量4kg/sの燃焼用空気を燃焼器に供給することができ、実圧実温での性能評価が可能となった。
DescriptionJAXA Research and Development Memorandum
宇宙航空研究開発機構研究開発資料
Keywordstest facility; combustion chamber; combustion; engineering drawing; engine test; fuel system; exhaust system; high temperature combustion; high pressure combustion; traversing measurement system; Moonlight Project; low-Nox fuel injector; 試験設備; 燃焼器; 燃焼; 製図; エンジン試験; 燃料系; 排気系; 高温燃焼; 高圧燃焼; 移動測定システム; ムーンライトプロジェクト; 低窒素酸化物燃料噴射器
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
SHI-NOAA0063150000
Report NoJAXA-RM-05-007
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/44139


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