Injector for LOX-GH Stable Combustion at Low Pressure and High Velocity

A novel injector is proposed in response to "Robust design solutions for liquid oxygen injection and subsequent stable combustion with high temperature (5100 Rankine / 2850 K) hydrogen flowing at low pressure (3-15 psia) and high velocity (~Mach 0.2)" subtopic, listed under "Advanced Propulsion Systems Ground Test Technology" focus area. This injector features fully 3D-printed Liquid Oxygen (LOX)-centered swirl coaxial design with high-speed hydrogen flowing peripherally and impinging axially on central LOX conical spray. We believe that due to ability of the center swirl element to atomize LOX to a fine degree and penetrate into Gaseous Hydrogen (GH) free stream, this injector would be able to ignite with hot GH without a separate ignition system, and sustain combustion thereafter in a stable and efficient manner. Because of its potential to be easily tunable in response to combustion dynamics observed in operation, we expect to develop this injector for a stable operation at a rapid pace. This injector can be used in any system flowing hot high-speed hydrogen or hydrogen-rich mixture needed to be burned or neutralized, such as NASA's ground testing of nuclear rocket engines or similar hydrogen-rich combustion devices. Phase I will focus on technical feasibility demonstration and procurement of two sub-scale prototype injectors, with and without premix of LOX-GH propellants upstream of primary combustion zone, completing at TRL 2. If this project proceeds into Phase II, it will focus on sub-scale and full-scale hot-fire development testing and demonstration, for follow-on commercialization and field operations, completing at TRL 6.

NASA Ground testing of nuclear thermal propulsion NASA Ground testing of hydrogen rich rocket engines

Nuclear reactor coolant hydrogen combustion Liquid air cycle engines - thrust augmentation Ram / Scramjet combustion Air-augmented rockets Research test article at government and university labs

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