Analysis of coolant flow and heat transfer in the SSME HPOTP Number 4 bearing assemblyThe PHOENICS code has been applied to simulate the flow of liquid oxygen through the number 4 ball bearing assembly of the Space Shuttle Main Engine High-Pressure Oxidizer Turbopump. The Body-Fitted Coordinate system capability of PHOENICS was utilized to create a geometrically accurate model. Effects accounted for by the model include the rotation rate of the calculation domain, viscous heating in the liquid oxygen and two-phase effects due to LOX boiling. A separation program was used to account for conduction within a ball bearing element which was coupled with the PHOENICS flow and heat transfer analysis. Solutions have been obtained for the velocity and temperature fields within the LOX coolant and the temperature within the ball element. The predicted ball temperatures indicate that the coolant is boiling in the region near the ball surface.
Document ID
19900032598
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Owens, S. F. (CHAM of North America, Inc. Huntsville, AL, United States)
Costes, N. C. (NASA Marshall Space Flight Center Huntsville, AL, United States)