Computational and Experimental Investigation of Transverse Combustion Instabilities
Abstract
Concurrent experiments and computations are used to analyze combustion instabilities in a transverse mode combustion chamber. The experiments employ a shear-coaxial injector element, positioned within a rectangular chamber. The reacting flow portion of the study element is optically accessible and the chamber is extensively instrumented with high-frequency pressure transducers. High amplitude transverse acoustics modes are driven by unstable injector elements located near the chamber end-walls. Different levels of instability are obtained by varying the operation of these driving elements. High-fidelity computational fluid dynamics simulations are used to model this set-up, although only the study element is fully represented and the transverse acoustics modes are generated by vibrating the side walls at the appropriate frequencies. The computational results are compared quantitatively with the high frequency pressure measurements, and qualitatively by using the CH* chemiluminescence signal from the experiment. The combustion response of the first, second and third transverse modes obtained using a dynamic modal decomposition procedure show excellent agreement between the experiments and simulations. The overall approach shows significant promise for screening the combustion response of candidate injector configurations for rocket applications.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2013
- Accession Number
- ADA596109
Entities
People
- Collin Morgan
- Kevin Shipley
- Matthew E. Harvazinski
- Venkateswaran Sankaran
- William E Anderson
Organizations
- Air Force Research Laboratory