This paper examines current research efforts underway at Lewis Research Center which have focused on improving the structural durability of the SSME turbodrive system through more fully examining the aerothermodynamics of the flow system. This objective was achieved by developing three-dimensional viscous and inviscid computer codes to predict the pressure and temperature distributions in the engine flow passages, particularly within the SSME turbines and turnaround ducts.
Application of Viscous and Inviscid Computation Methods for Rocket Turbopump Systems
Sae Technical Papers
Aerospace Congress and Exposition ; 1984
1984-10-01
Aufsatz (Konferenz)
Englisch
Liquid rocket engine turbopump inducers
NTRS | 1971
|Viscous and Inviscid Vortex Generation During Startup of Rocket
Online Contents | 1998
|Reusable Rocket Engine Turbopump Condition Monitoring
SAE Technical Papers | 1984
|Reusable rocket engine turbopump condition monitoring
NTRS | 1985
|