ROCKET PROPULSION SYSTEMS LLC — National Aeronautics and Space Administration SBIR Phase I: H10

Description

A novel injectornbsp;is proposed in response to quot;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)quot; subtopic, listed undernbsp;quot;Advanced Propulsion Systems Ground Test Technologyquot; focus area.nbsp; This injector features fully 3D-printed Liquid Oxygen (LOX)-centered swirl coaxial design with high-speed hydrogen flowing peripherally andnbsp;impinging axiallynbsp;on central LOX conical spray.nbsp; 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.nbsp; Because of its potentialnbsp;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.nbsp; This injector can be used in any systemnbsp;flowing hot high-speed hydrogen or hydrogen-rich mixture needed to be burned or neutralized, such asnbsp;NASA#39;s ground testing of nuclear rocket enginesnbsp;or similar hydrogen-rich combustion devices.nbsp; 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.nbsp; If this project proceeds into Phase II, it will focus on sub-scale and full-scale hot-fire development testing and demonstration, for follow-onnbsp;commercialization and field operations, completing at TRL 6.nbsp;nbsp;nbsp; nbsp;nbsp;nbsp; nbsp;