The aerodynamic design of advanced fuel and oxidizer pump drive turbines is described. The technology represented by these new configurations is being devloped for application in the main propulsion system for the U.S. Government's National Launch System now in the preliminary design phase. The main engines for this system will use a gas generator cycle and produce over 600,000 pounds of thrust, with throttling capability. The pump drive turbine design requirements defined by the advanced gas generator engine cycle specify very high specific work in order to minimize gas generator system flow and maixmize specific impulse. The high work requirements combined with the relatively low rotational speeds needed by the cryogenic pumps, result in high turbine stage loadings. The detail design process, along with the final baseline fuel and oxidizer turbine configurations are presented. Computed airfoil surface static pressure distributions and flow charcteristics are shown. The turbine designs described, are the result of a successful team working relationship in which numerous individuals from different organizations worked together in a complementary and synergistic manner. Both turbine configurations employ 'unconventional' high turning blading, (approx. 160 deg.) and are predicted to provide significant cost and performance benefits relative to traditional configurations.
Design of advanced turbopump drive turbines for national launch system application
Die Auslegung von verbesserten Turbinen mit Turbopumpenantrieb für Anwendungen bei nationalen Raumfahrzeugsystemen
AIAA-Papers ; 1-10
1992
10 Seiten, 13 Bilder, 5 Tabellen, 5 Quellen
Conference paper
English
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