Protrusion effect on the performance of hybrid rocket with liquefying and non-liquefying fuels

Dinesh, Mengu; Rajput, Saideep Singh; Kumar, Rajiv

doi:10.1016/j.actaastro.2020.09.039

Cited by 21 publications

(20 citation statements)

References 22 publications

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“…Grosse [12] Wax-N 2 O Experimental Effect of single-hole and multi-hole protrusion configurations on regression rate and combustion efficiency Dinesh and Kumar [13][14] Wax-GOX Experimental Effect of nylon-based single and multi-protrusion on regression rate and combustion efficiency Dinesh et al [15] PVC-Gox Wax-Gox Experimental Effectiveness of protrusion in improving the regression rate and combustion efficiency in two different fuels exhibits different combustion behavior. Kumar and Ramakrishna [16] Wax-GOX Experimental Effect of graphite and rubber protrusion on regression rate and combustion efficiency in conjunction with bluff-body at the head end Kumar and Kumar [17] HTPB-GOX CFD Numerical Investigations on Effect of various parameters related to protrusion on regression rate and combustion efficiency Bellomo et al [18] Wax-N 2 O CFD Computational investigations of Grosse [12] work Sun et al [19] PE-…”

Section: Aim Of Investigationmentioning

confidence: 99%

“…In this study, the authors have observed a significant improvement in the regression rate while using the three pro-trusions in the combustion chamber. Dinesh et al [15] studied the effectiveness of the protrusion on the regression rate of two different solid fuels exhibiting different combustion behaviours. Their results showed that the relative improvement in regression is the same for both fuels.…”

Section: Introductionmentioning

confidence: 99%

“…In the past two decades, the interest in utilizing the protrusion method in hybrid rockets has been increasing due to its benefits over other methods [12][13][14][15][16][17][18][19][20][21][22][23][24]. The significant research contributions on the protrusion method in the hybrid rocket are compiled in Table 1.…”

Section: Introductionmentioning

confidence: 99%

“…Usually, this phenomenon occurs while moving from head end to the nozzle end hence, it causes the reduction in regression rate. In this scenario, when the protrusion is placed in the combustion chamber, it disturbs the boundary layer and forms the recirculation behind it [13][14][15][16][17]. This recirculation re-attaches to the fuel surface while dragging the hot product gases towards the fuel surface and then the boundary layer re-develops to the downstream direction.…”

Section: Introductionmentioning

confidence: 99%

“…More details regarding the utilization of the protrusion method in the hybrid rocket motor can be found in Refs. [13][14][15][16][17].…”

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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