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High Efficiency Rotating Detonation Combustor for Augmentors

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-22-C-0668
Agency Tracking Number: N21A-T011-0065
Amount: $999,998.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: N21A-T011
Solicitation Number: 21.A
Solicitation Year: 2021
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-08-30
Award End Date (Contract End Date): 2024-09-12
Small Business Information
20 New England Business Center
Andover, MA 01810-1111
United States
DUNS: 073800062
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Jeffrey Wegener
 (978) 738-8164
Business Contact
 William Marinelli
Phone: (978) 738-8226
Research Institution
 University of Michigan Transportation Research Institute
 Raymond Cluckey
3003 South State Street
Ann Arbor, MI 48109-1274
United States

 (734) 764-2329
 Nonprofit College or University

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. In Phase I, University of Michigan evaluated the technology using computational evaluations of RDCs in multi-fidelity simulations, while PSI completed more than 150 hot fire tests of several RDC design configurations using gaseous hydrogen fuel. In Phase II, these designs will be evaluated using JP-5 fuel and high-temperature, oxygen-deprived air in order to simulate augmentor inlet conditions, creating a performance data package for Navy Program Offices and OEMs pursuing performance enhancement of future systems.

* Information listed above is at the time of submission. *

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