PHYSICAL SCIENCES INC. — Department of Defense STTR Phase I: N21A-T011

Description

Physical Sciences Inc. (PSI) and University of Michigan will design, develop, and demonstrate a rotating detonation combustor (RDC) for gas turbine engine augmentors. This program advances a novel combustor design based on a unique geometric approach that addresses the stability and efficiency issues that have prevented RDCs from reaching performance metrics predicted by theory. Flow uniformity is improved in the combustor and the combustor exit by decreasing pressure fluctuations and discontinuities. The integrated combustor and combustor exit geometry allows this innovation to be used for RDC-based pilot detonation for augmentors or for a full detonation RDC-based augmentor. PSI achieves these benefits using low mean chamber pressures to capitalize on the pressure-gain nature of detonation engine cycles. These benefits will significantly reduce the size of augmentors. PSI has previously demonstrated the performance benefits of this technology in ground-based rotating detonation rocket engine firings up to 200 lbf of thrust. In the Phase I STTR, PSI and University of Michigan will evaluate the technology for augmentor applications using experimental and computational evaluations of RDCs with augmentor inlet conditions. The Phase I will maximize risk reduction by obtaining hot fire data for an air-breathing RDC having a nominal diameter of 6 inches.