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Combustion Stability Characteristics of the Model Chamber with Various Configurations of Triplet Impinging-Jet Injectors  

Sohn Chae-Hoon (Department of Aerospace Engineering, Chosun University)
Seol Woo-Seok (Rocket Engine Department, Korea Aerospace Research Institute)
Shibanov Alexander A. (Research Institute of Chemical Machine Building (NIICHIMMASH), Sergiev Posad)
Publication Information
Journal of Mechanical Science and Technology / v.20, no.6, 2006 , pp. 874-881 More about this Journal
Abstract
Combustion stability characteristics in actual full-scale combustion chamber of a rocket engine are investigated by experimental tests with the model (sub-scale) chamber. The present hot-fire tests adopt the combustion chamber with three configurations of triplet impinging-jet injectors such as F-O-O-F, F-O-F, and O-F-O configurations. Combustion stability bound-aries are obtained and presented by the parameters of combustion-chamber pressure and mixture (oxidizer/fuel) ratio. From the experimental tests, two instability regions are observed and the pressure oscillations have the similar patterns irrespective of injector configuration. But, the O-F-O injector configuration shows broader upper-instability region than the other configurations. To verify the instability mechanism for the lower and upper instability regions, air-purge acoustic test is conducted and the photograph or the flames is taken. As a result, it is found that the pressure oscillations in the two regions can be characterized by the first impinging point of hydraulic jets and pre-blowout combustion, respectively.
Keywords
Combustion Stability; Stability Boundary; Hot-Fire Test; Model Chamber; Triplet Impinging-Jet Injectors;
Citations & Related Records
Times Cited By KSCI : 4  (Citation Analysis)
Times Cited By Web Of Science : 0  (Related Records In Web of Science)
Times Cited By SCOPUS : 0
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