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Numerical Prediction of Transient Axial Thrust and Internal Flows in a Rocket Engine TurbopumpThis paper presents the application of the Generalized Fluid System Simulation Program (GFSSP) to model the time-dependent flow in a complex secondary flow circuit of the turbopump of the Fastrac engine currently under development at Marshall Space Flight Center. GFSSP is a general purpose computer program for analyzing steady-state and time-dependant flowrates, pressures, temperatures, and concentrations in a complex flow network. The program employs a finite volume formulation of mass, momentum and energy conservation equations in conjunction with the thermodynamic equation of state of real fluids. GFSSP was used to calculate the axial thrust and internal flow distribution of the Fastrac engine turbopump during the start and shut down transients. The models discussed in this paper use boundary conditions that were extracted from turbopump test data. The GFSSP predicted turbopump secondary flow passage pressures and temperatures were compared with actual measured values.
Document ID
19990069943
Acquisition Source
Marshall Space Flight Center
Document Type
Reprint (Version printed in journal)
Authors
VanHooser, Katherine
(NASA Marshall Space Flight Center Huntsville, AL United States)
Bailey, John W.
(Sverdrup Technology, Inc. Huntsville, AL United States)
Majumdar, Alok
(Sverdrup Technology, Inc. Huntsville, AL United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Subject Category
Fluid Mechanics And Heat Transfer
Meeting Information
Meeting: Joint Propulsion
Location: Los Angeles, CA
Country: United States
Start Date: June 21, 1999
Sponsors: American Society for Electrical Engineers, Society of Automotive Engineers, Inc., American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAS8-40386
Distribution Limits
Public
Copyright
Other

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