Abstract
Abstract A numerical model has been developed to predict the fast transient spray-combusting flows. This method is pressure based, noniterative, and applicable to flows at all speeds. Special emphasis is given to the overall behavior of nonlinear combustion instabilities in the liquid-fueled rocket engines. Computations were carried out for various combustion parameters such as initial spray conditions and baffle lengths. The present numerical model successfully predicts high-frequency combustion instability as well as fast transient flow. The baffle length as well as variations in droplet size have significant effects on engine stability. The numerical results indicate that the baffle can effectively suppress pressure oscillations.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
