The mechanisms controlling hypergolic propellant reactive stream separation (RRS) were studied and used to develop design criteria for injectors free from both steady state RSS and cyclic propellant stream separation. This was accomplished through the analysis of single element injectors using N204/MMH propellants; the injectors were representative of the space shuttle orbit maneuvering engine and space tug applications. A gas phase/surface reaction mechanism which controls RSS was identified. Injector design criteria were developed, which defined a critical chamber pressure for those operating conditions above which RSS occurs. It was found that the amount of interfacial surface area at impingement is controlled by injector hydraulics.
High Performance N2O4/Amine Elements: Blowapart
1977
268 pages
Report
Keine Angabe
Englisch
Combustion & Ignition , Manned Spacecraft , Fuel injection , Jet mixing flow , Rocket engine design , Thrust chambers , Rocket propellants , Separated flow , Nitrogen tetroxide , Space shuttle orbiters , Stream functions (Fluids) , Turbulent mixing , Hypergolic rocket propellants , Methyl hydrazines
High Performance N2O4/Amine Elements
NTIS | 1976
|High performance N2O4/amine elements
NTRS | 1976
|High Performance N2O4/Amine Elements
NTRS | 1976
|High performance N2O4/amine elements: Blowapart
NTRS | 1977
|NTRS | 1986
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