Effects of Propellant Momentum Ratio on Combustion Behavior in an Ethanol/Liquid Oxygen Rocket Engine Combustor with a Planar Pintle-type Injector
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- KAKUDO Hiromitsu
- 東京大学大学院工学系研究科航空宇宙工学専攻
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- SAKAKI Kazuki
- 連絡先著者(Corresponding author):kazuki-sakaki@g.ecc.u-tokyo.ac.jp 東京大学大学院工学系研究科航空宇宙工学専攻
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- NAKAYA Shinji
- 東京大学大学院工学系研究科航空宇宙工学専攻
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- TSUE Mitsuhiro
- 東京大学大学院工学系研究科航空宇宙工学専攻
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- KANAI Ryuichiro
- インターステラテクノロジズ株式会社
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- INAGAWA Takahiro
- インターステラテクノロジズ株式会社
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- HIRAIWA Tetsuo
- 国立研究開発法人宇宙航空研究開発機構
Bibliographic Information
- Other Title
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- エタノール/液体酸素ロケットエンジン燃焼室における平面ピントル型噴射器の推進剤噴射運動量比が燃焼挙動に及ぼす影響
- エタノール/エキタイ サンソ ロケットエンジン ネンショウシツ ニ オケル ヘイメン ピントルガタ フンシャキ ノ スイシンザイ フンシャ ウンドウリョウヒ ガ ネンショウ キョドウ ニ オヨボス エイキョウ
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Description
The pintle injector is a promising candidate for injection systems of future rocket engines because of the throttling capability, the combustion stability, and the low manufacturing cost. Few studies focusing on fundamental aspects of a pintle injector have been conducted, and most of the design parameters of a pintle injector is determined mainly based on the empirical knowledge. Among the design parameters, total momentum ratio (TMR) is one of the most important parameters since spray structure is dominated by TMR. Therefore, combustion experiments using an ethanol/liquid oxygen rocket engine combustor with a planar pintle-type injector which is designed for optical measurements for a pintle injector are conducted at combustion pressure (Pc) = 0.37-0.42MPa, mixture ratio (O/F) = 1.31-1.49, TMR = 0.32-3.65 to investigate the effects of propellant momentum ratio on the combustion behavior. The spray structure under hot fire conditions is observed using high-speed imaging techniques with a backlit configuration. In the oxidizer-centered configuration, the characteristic exhaust velocity efficiency (ηC*) decreases with the increase of the TMR. The atomized propellant impinge on the combustor wall before the vaporization and reaction at higher TMR. In the fuel-centered configuration, though the propellant spray is more inclined to the direction of the upper combustor wall at higher TMR, the ηC* does not change with the TMR. In both oxidizer-centered and fuel-centered, higher ηC* is provided in the condition of higher injection pressure drop.
Journal
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- JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 65 (1), 1-9, 2017
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Details 詳細情報について
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- CRID
- 1390282679445097600
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- NII Article ID
- 130005316526
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- NII Book ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL BIB ID
- 027925919
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL Search
- Crossref
- CiNii Articles
- KAKEN
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- Abstract License Flag
- Disallowed