Experiments on liquid hydrogen turbopump for rocket engine
Experiments on liquid hydrogen turbopump for rocket engine
- Neue Suche nach: Tanatsugu, N.
- Neue Suche nach: Kuratani, K.
- Neue Suche nach: Tanatsugu, N.
- Neue Suche nach: Kuratani, K.
The development of LH 2/LOX rocket engine is being conducted in Institute of Space and Aeronautical Science, University of Tokyo. This paper describes the liquid hydrogen turbopump for rocket engine. The turbopump was designed to feed liquid hydrogen into the thrust chamber of 7000 kg thrust level, and has the capabilities of head rise of 5900 m and flowrate of 2.90 kg/sec at the rated rotational speed of 44000 rpm. The pump is a single-stage, centrifugal-flow type with a helical inducer and a single volute casing. The impeller of the pump, 130 mm in diameter, consists of 24 blades with a discharge angle of 90 degrees. The axial thrust loaded on pump shaft is balanced by decreasing the pressure behind the impeller to an adequate level with the aid of 24 small radial vanes. The pump is driven by a single-stage impulse turbine. (Wassmann)
Dokumentinformationen
Experiments on liquid hydrogen turbopump for rocket engine
Versuche mit einer Fluessigwasserstoff-Turbopumpe fuer Raketenantriebe
Cryogenic Engineering ; 15 , 2 ; 38-45
1980
8 Seiten, 16 Bilder, 4 Tabellen, 15 Quellen
Aufsatz (Zeitschrift)
Japanisch
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