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.