A 60,000 lb trust liquid Oxygen (LOX) and rocket propellant #1 (RP-1) rocket engine is being developed at the Marshall Space Flight Center (MSFC) as part of NASA's ongoing effort to lower the cost of access to space. The goal of the program is to demonstrate a low cost rocket engine with acceptable performance. In order to reduce design and development risk, computational fluid dynamics (CFD) analysis was used extensively in the design process, especially in the design of the turbopump. This paper documents the process used and significant results obtained during the design of the LOX and RP-1 pumps. This includes the design of the inlet manifolds, the integral inducer-impellers, the diffusers, and the collector volutes. The resulting designs incorporate low-cost design features while meeting the engine cycle requirements.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Hydrodynamic Design of the Fastrac Turbopump


    Contributors:

    Publication date :

    1998-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English




    Hydrodynamic Design of the Fastrac Turbopump

    R. Garcia / R. Williams / S. Fears | NTIS | 1998



    Observations on Rotating Cavitation and Cavitation Surge From the Development of the Fastrac Engine Turbopump

    Zoladz, T. / American Institute of Aeronautics and Astronautics / Society of Automotive Engineers et al. | British Library Conference Proceedings | 2000


    Fastrac nozzle design, performance and development

    Peters, Warren / Rogers, Patrick / Lawrence, Timothy et al. | AIAA | 2000


    Fastrac Nozzle Design, Performance and Development

    Peters, W. / Rogers, P. / Lawrence, T. et al. | British Library Conference Proceedings | 2000