Rotating Detonation Flameholder for Augmenting High-Speed Combustor Performance
Abstract
Effects of applying rotating detonation engine (RDE) flowfield on supersonic combustor as a possible flameholder and mixing enhancement device are to be investigated by analyzing pertinent experimental data, assessing relative contributions of coupled physical processes, and enhancing our understanding of transient compressible reacting mixing layer with impulsively applied cross-shear stress imposed by the wave-induced flows. The flowfield associated with integrating RDE with a scramjet combustor would lead to complex physical interactions between a supersonic jet of partially-mixed reactant flow, associated wake flow at the flow separation point, and transient azimuthal flow structures generated by rotating detonation waves encircling the central reactant jet. Between the main supersonic jet flow and the surrounding rotary flow field dominated by detonation wave structures, a transient reacting compressible mixing layer is formed with impulsively applied cross-shear introduced by periodically generated wave-induced flow structures. The main objectives of this project are to characterize and analyze the transient interaction occurring in this cross-flow mixing layer and to study underlying physical mechanisms while providing science and engineering support for systematic evaluation of the experimental model and component designs. The approaches will involve a combination of data-based analytical studies, subsequent theoretical computations, and experimental studies to better understand the flowfield and the underlying physics. The dominant physical mechanisms affecting supersonic combustor performance with the use of an RDE flameholder will be studied for propulsion applications. Of particular interest is the role of detonation-wave-induced flow excitation on the growth and stability of turbulent reacting compressible shear layer formed between periodically surging detonation wave flowfield and steady supersonic jet of reactant core flows.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 14, 2024
- Source ID
- FA95502310757
Entities
People
- Kenneth Yu
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Maryland