Physical characterization and elucidation of the detonation engine, detailed analysis of supersonic flow field, and innovative simulation for chemical reaction tracing
Abstract
In this study, the applicants are responsible for fabricating a small detonation combustor and for fully elucidating the mechanism of supersonic jet generation without a throat and film-cooled detonation chamber. By our new method, it is possible to realize a long durability at high heat flux. We will construct a turbine that is supersonic in all regions within the turbine blades. Since the flow path expands outward with the entrance near the center axis, weight can be reduced to the same extent as that of an axial-flow turbine. Innovative TD-GW real ab initio computer simulation to trace fuel burning with catalyst will be performed to understand clearly the burning process in detail, which is not possible to be understood only by experimental works.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Feb 16, 2024
- Source ID
- FA23862314061
Entities
People
- Yoshiyuki Kawazoe
Organizations
- Air Force Office of Scientific Research
- United States Air Force