NASA and Aerojet are developing a Rocket-Based Combined Cycle (RBCC) engine under the Advanced Reusable Technology program. The rocket application requires that the combustion process be stable, complete, and take place in as short a distance as possible without compromising the structural integrity of the injector itself. A novel gaseous hydrogen-oxygen rocket injector element design was arrived at through an iterative design process making extensive use of CFD simulations, which resulted in a design that is meeting design goals. Sub-scale versions of the injector have been built and tested in a unique test-rig and in a sub-scale RBCC engine. The Aerojet RBCC concept integrates small rocket thrusters into the rearfacing base area of struts placed in the flowpath of a scramjet (Supersonic Combusting Ramjet) engine. In one mode of operation, at vehicle takeoff, the rockets provide the primary thrust with additional thrust coming from an ejector effect as air is drawn into the engine inlet, entrained, and accelerated by the rocket exhaust.
Design of a Novel Gaseous Hydrogen-Oxygen Rocket Injector Element
Fluent Users'' Group Meeting ; 1999 ; Danvers, MA, United States
1999-01-01
Miscellaneous
No indication
English
Gaseous Hydrogen/Oxygen Injector Performance Characterization
British Library Conference Proceedings | 1994
|Gaseous Hydrogen/Oxygen Injector Performance Characterization
British Library Conference Proceedings | 1994
|