Shock wave and combustion dynamics in high speed perisymmetric flow paths
Abstract
This proposal outlines an effort to understand the physicochemical interaction between shock wave propagation and combustion dynamics in canonical perisymmetric flow paths for ram-scram transition (~Mach 4.5) and full scram (Mach 7) regimes. The project will utilize high speed 3D laser diagnostics and numerical analysis methods to understand the basic physics underlying shockwave dynamics and combustion stability in perisymmetric geometries. In doing so, we will attempt to gain a fundamental understanding of operational conditions that can lead to instabilities in supersonic conditions. An experimental effort will be undertaken in an optically accessible perisymmetric flow path model in the free flow high enthalpy flow tunnel, ACT-II, where spatially resolved high speed diagnostics such as (1) 3D PLIF exceeding 100 kHz, (2) particle induced scattering, (3) nano-second LIBS, and (4) high speed schlieren will be carried out for measurements of the isolator, cavity, and the combustor regions simultaneously. The unprecedented visualization of the relevant phenomena will yield means to extract the key physics that control the interaction between the isolator flow dynamics and combustion stability for critical ram to scram transition regimes and full scram conditions. We seek to identify physical parameters that can be scaled up to practical scramjet models. The work will be conducted in close collaboration with both research partners at the University of Queensland (Center for Hypersonics), Australian Defense Science and Technology Office (DST) and AFRL. By extending the limits of state-of-the-art diagnostics and applying it to well defined reactive flows in realistic high speed conditions, the study will offer optimized design guidelines for more advanced future propulsion systems that can operate smoothly over a wider al envelope than what is conventionally available today.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 21, 2022
- Source ID
- FA95502110072XX0
Entities
People
- Tonghun Lee
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Illinois Urbana–Champaign