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Design of a Novel Gaseous Hydrogen-Oxygen Rocket Injector ElementNASA 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.
Document ID
19990063761
Acquisition Source
Marshall Space Flight Center
Document Type
Reprint (Version printed in journal)
Authors
Glenn, Dennis E.
(GenCorp Aerojet Sacramento, CA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Fluent Users'' Group Meeting
Location: Danvers, MA
Country: United States
Start Date: May 26, 1999
Funding Number(s)
CONTRACT_GRANT: NAS8-40891
Distribution Limits
Public
Copyright
Other

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