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Completed TRL 5 (started at 2, targeting 5)
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. 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. Current TRL = 1: Basic Principles observed and reported Example paper: Nordeen, C. A., Schwer, D., Corrigan, A. T., and Cetegen, B., "Radial Effects on Rotating Detonation Engine Swirl," AIAA Propulsion and Energy 2015 Forum, American Institute of Aeronautics and Astronautics, AIAA 2015-3781, 2015. https://doi.org/10.2514/6.2015-3781 TRL Progression 2&3: Technology concept formulated and analytical critical function demonstration via this proposal "NASA Phase I SBIR 2023 subtopic A1.09 application: “Rotating Detonation X-Combustor (RDXC) Turbine Integration Program”. RDXC 1-D Analytic Model correlated with 3-D CFD simulation with detailed geometry, operability and performance maps. TRL Progression 4&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.
A flight-weight subscale engine will support subscale H2 zero emissions and integrated aircraft studies of hybrid aircraft (SUSAN) and drone-scale autonomous aircraft. The RDXC can be adapted to rocket engines with conventional nozzles and a variety of fuels.
A production subscale RDXC supports H2 fueled drone-scale autonomous aircraft. Microturbine power generation would benefit substantially from the increased cycle The full scale RDXC support H2 fueled transport aircraft i.e. SUSAN.
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