Developmental History of Liquid Oxygen Turbopumps for the LE-7 Engine.
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- Kamijo Kenjiro
- Tohoku University, Institute of Fluid Science
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- Yamada Hitoshi
- National Aerospace Laboratory, Kakuda Research Center
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- Sakazume Norio
- National Space Development Agency of Japan
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- WARASHINA Shogo
- Ishikawajima-Harima Heavy Industries Co.
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The first stage of the H-2 rocket used a 110-ton thrust liquid oxygen, liquid hydrogen, pump-fed engine, the LE-7. This engine required high-pressure and high-power liquid oxygen and liquid hydrogen turbopumps to achieve the two-stage combustion cycle in which the combustion pressure is around 13 MPa. Furthermore, it was very important to operate both turbopumps at higher rotational speeds to obtain a smaller, lighter-weight engine because the LE-7 had not low-speed, low-pressure pumps ahead of both the main pumps. The present paper shows the design, test results, and modifications that had been performed until a flight-type liquid oxygen turbopump for the LE-7 engine was completed. The liquid oxygen turbopump had been developed by the use of three models, that is, research, prototype, and flight models.
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 44 (145), 155-163, 2001
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390001204078739584
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- NII論文ID
- 10007198522
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- NII書誌ID
- AA0086707X
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- ISSN
- 21894205
- 05493811
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- NDL書誌ID
- 5993875
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- NDL
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