Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
National Space Development Agency of Japan(NASDA)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-1130
The liquid oxygen turbopump for the LE-7 rocket engine is driven by fuel enriched hot gas, and has a helium purge seal placed between the pump and the turbine to separate the turbine drive gas from the oxygen. An experimental study on a carbon segmented circumferential seal with Rayleigh steps was conducted in order to develop a helium purge seal with low leakage and high durability. The experimental and analytical results concerning the sealing characteristics of this carbon segmented seal are described, with comparisons between these result showing that the effects of both the seal pressure and rotational speed on the leakage rate are fairly dependent on the opening force induced by the Rayleigh steps. Since the carbon sealing surface was worn in conformity with the profile of the deformed runner sealing surface, the time dependent relationships which exist between the static/dynamic leakage rates and the sealed pressure, which are caused by progression of carbon wear, were clarified.
液体酸素ターボポンプ用セグメントシールの密封特性
naltr01130.pdf
(1.56MB)
