Combustion Dynamics in Postchamber of Hybrid Rocket Using CH* Radical Chemiluminescence Images

Choi, Go Eun; Moon, Young Joo; Lee, Changjin

doi:10.2514/1.b35999

Cited by 7 publications

(2 citation statements)

References 16 publications

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“…This shear layer forms unstable waves due to the surrounding disturbances and rolls up to form coherent structures of vortices [30]. In a hybrid rocket, the possible areas where the vortex shedding occurs are pre-and post-combustion chambers [32]. In addition to these, the insertion of protrusions [13], cavities [22], and bluff bodies [23] in the combustion chamber can also produce the vortex shedding in a hybrid rocket.…”

Section: Aim Of Investigationmentioning

confidence: 99%

“…However, the combustion instabilities in hybrid rockets have to be dampened because; they can create mechanical vibrations that cause damage to the control systems, payloads, and other structural parts of the launch vehicle. Several researchers have tried to understand the combustion instabilities in hybrid rockets under a wide range of operating conditions and fuel-oxidizer combinations [27][28][29][30][31][32][33]. Based on these studies, the classification of combustion instabilities and their driving mechanism in hybrid rockets are summarized in Table 2.…”

Section: Introductionmentioning

confidence: 99%

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Effect of Protrusion on Combustion Stability of Hybrid Rocket Motor

Dinesh

Kumar

2022

Propellants Explo Pyrotec

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In hybrid rockets, low regression rate and low combustion efficiency are major drawbacks restricting its utilization in practical applications. Inserting a protrusion in a hybrid rocket combustion chamber is one of the methods to enhance the regression rate and combustion efficiency. In the present study, while utilizing the protrusion method the combustion stability of the hybrid rocket was investigated. The protrusions used for this study were of two different types; one was made of graphite and another one was nylon. The nylon protrusion can regress during the combustion along with the fuel whereas, graphite cannot. Before using the protrusion method, the combustion stability of the hybrid rocket motor (base case) was characterized. During the combustion of the base case motor, intense pressure oscillations were observed for a definite period after the beginning of the combustion. These oscillations were found to be the result of the interaction between the vortex shedding and fundamental longitudinal acoustic modes of the chamber at the fuel grain exit. Upon inserting the protrusion near the fuel grain exit, significant suppression in the pressure oscillations was observed. A 96 % reduction in amplitude of acoustic modes relative to the base case was observed. There was no substantial difference in combustion stability of the hybrid rocket when using graphite or nylon protrusions. Further, it was realized that the combustion stability of the rocket motor remains unchanged even after varying the thickness of the protrusion at 0.8X/L location.

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