Rotating Detonation X-Combustor (RDXC) Turbine Integration Program

The Rotating Detonation X-Combustor - Turbine Integration Program (PDXC-TIP) will develop a novel pressure gain combustor that is integrated with a turbine and engine configuration. The x-combustor is designed to improve turbine efficiency by attenuating effects of the detonation. The RDXC/turbine pair is integrated into a gas turbine architecture to support zero emission technologies for aircraft. The overall engine design supports electric-hybrid aircraft architectures with integrated electrical generators and motors. nbsp;The pressure gain combustion will boost the efficiency of a hydrogen-fueled gas turbine and offset potential installation costs of hydrogen. The use of hydrogen eliminates any carbon-based combustion products. The very short combustion time reduces the creation of NOx products. nbsp;Current TRL = 1: Basic Principles observed and reportedExample paper: Nordeen, C. A., Schwer, D., Corrigan, A. T., and Cetegen, B., quot;Radial Effects on Rotating Detonation Engine Swirl,quot; AIAA Propulsion and Energy 2015 Forum, American Institute of Aeronautics and Astronautics, AIAA 2015-3781, 2015. https://doi.org/10.2514/6.2015-3781nbsp;TRL Progression 2amp;3: Technology concept formulated and analytical critical function demonstration via this proposal quot;NASA Phase I SBIR 2023 subtopic A1.09 application: ldquo;Rotating Detonation X-Combustor (RDXC) Turbine Integration Programrdquo;.nbsp;RDXC 1-D Analytic Model correlated with 3-D CFD simulation with detailed geometry, operability and performance maps.TRL Progression 4amp;5: Breadboard validation in a laboratory environment and then validation in a relevant environment via Phase 2 of this program. NASA Phase II SBIR 2023 subtopic A1.09 application: (1) DXC/Turbine Test Rig demonstrates shock and swirl attenuation and turbine efficiency gain or equivalent constant pressure efficiency, (2) RDXC Engine Test Rig demonstrates complete engine cycle efficiency.nbsp;nbsp;