@techreport{oai:jaxa.repo.nii.ac.jp:00045095,
 author = {若松, 義男 and 冠, 昭夫 and 都木, 恭一郎 and WAKAMATSU, Yoshio and KANMURI, Akio and TOKI, Kyoichiro},
 month = {Sep},
 note = {上段用小形液酸/液水ロケットエンジンには,エキスパンダーサイクルやクーラントブリードサイクルが推奨されている。これはシステムの高性能化と単純化を計るためであるが,両サイクル共に長短を有する。本研究では,LH2ポンプをエキスパンダータービンで,LOXポンプをブリードタービンで駆動し,かつブリードによる比推力の損失を最小におさえ得る新しいエンジンサイクル,PBE(Partial Bleed Expander)サイクルについて検討を行った。この結果,本サイクルではシステム開発の容易性とエキスパンダーサイクルに非常に近い高性能とを合わせ持つことを期待できることが明らかとなった。, The expander cycle or the coolant bleed cycle LOX/LH2 engine is considered suitable for use with the orbit transfer vehicle and the upper stage of a conventional rocket because of their simplicity of engine system. However, these engine cycles generally require a thrust chamber with a high expansion area ratio in order to obtain a high performance and necessarily require a High Altitude Test Facility even in the initial phase of development. Here, the authors propose a new engine cycle called the "Partial Bleed Expander(PBE) cycle". In the PBE cycle, only the turbopump of one propellant(usually LH2) is driven in the expander cycle and a portion of fuel is bled to drive the turbopump of the of the other propellant (usually LOX). The bled fuel may be utilized for dump cooling or film cooling. From the calculation of the PBE cycle, it was made clear that the PBE cycle can perform at a level close to that of the expander cycle with the bleeding rate resulting in minimum Isp loss., 資料番号: NALTR0837000, レポート番号: NAL TR-837T},
 title = {PARTIAL BLEED EXPANDER CYCLE FOR LOW THRUST LOX/LH2 ROCKET ENGINE},
 year = {1984}
}