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AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsAlvin E. Buggele, John R. Gallagher
Estimating the term…
A family of supersonic injectors for use on spaceplanes, rockets and missiles and the like is disclosed and claimed. Each injector maintains a specific constant (uniform) Mach number along its length when used while being minimally intrusive at significantly higher injectant pressure than combustor freestream total pressure. Each injector is substantially non-intrusive when it is not being used. The injectors may be used individually or in a group. Different orientations of the injectors in a group promotes greater penetration and mixing of fuel or oxidizer into a supersonic combustor. The injectors can be made from single piece of Aluminum, investment cast metal, or ceramic or they can be made from starboard and port blocks strapped together to accurately control the throat area. Each injector includes an elongated body having an opening which in cross section is an hour glass (venturi shaped) and the opening diverges in width and depth from the bow section to the stem section of the opening.
A fuel injector comprising:
A fuel injector for a combustor comprising:
A fuel injector flush mounted in a combustor comprising an elongated body having proximate and distal portions;
An oxidizer or fuel injector system for injecting oxidizers or fuel into a supersonic cross flow having a specific Mach number, comprising:
Dependencies are inferred from the claim text.