Rotordynamics analysis of the Space Shuttle main engine high-pressure oxidizer pump

This study describes the rotordynamics analysis of the Space Shuttle Main Engine (SSME) high-pressure oxidizer turbopump. Modal synthesis methods were used to account for the complex coupling of the pump and engine structure. Cross-coupling elements effecting rotor stability were included in the analysis. Results of the analysis indicated that smaller bearing clearances and a smooth turbine interstage seal would result in longer bearing life and improved stability. Subsequent testing with these design features has shown the same results.