A combined Eulerian-Lagrangian two-phase flow analysis of SSME HPOTP nozzle plug trajectories. II - ResultsAn analysis of Space Shuttle Main Engine high-pressure oxygen turbopump nozzle plug trajectories has been performed, using a Lagrangian method to track nozzle plug particles expelled from a turbine through a high Reynolds number flow in a turnaround duct with turning vanes. Axisymmetric and parametric analyses reveal that if nozzle plugs exited the turbine they would probably impact the LOX heat exchanger with impact velocities which are significantly less than the penetration velocity. The finding that only slight to moderate damage will result from nozzle plug failure in flight is supported by the results of a hot-fire engine test with induced nozzle plug failures.
Document ID
19890059396
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcconnaughey, P. K. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Garcia, R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Dejong, F. J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Sabnis, J. S. (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Pribik, D. A. (Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)