One-dimensional modelling of the nozzle cooling with cryogenic oxygen flowing through helical channels in a hybrid rocket

Gallo, Giuseppe; Kamps, Landon T.; Hirai, Shota; Carmicino, Carmine; Nagata, Harunori

doi:10.1016/j.actaastro.2023.05.013

Cited by 7 publications

(2 citation statements)

References 17 publications

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“…It can be concluded that such a simple 1-D approach is not sufficient to perfectly reproduce the results of an experimentally validated, intensive numerical method. This mainly results from the use of the approximations presented by the Bartz correlation, Haaland equation, and Dittus-Boelter correlation as discussed in [43]. Particularly for LOX/LCH 4 engines, the Bartz correlation is reported to over-predict [44].…”

Section: Resultsmentioning

confidence: 99%

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Kose,

Celik

2023

Applied Sciences

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Due to the extreme temperatures inside the combustion chambers of liquid propellant rocket engines, the walls of the combustion chamber and the nozzle are cooled by either the fuel or the oxidizer in what is known as regenerative cooling. This study presents an indigenous computational tool developed for the analysis of heat transfer in regenerative cooling of such rocket engines. The developed tool incorporates a one-dimensional (1-D) combustion analysis to calculate the thermophysical properties of the combustion gas. Basic engine properties were calculated and used to generate a thrust chamber profile based on a bell-shaped nozzle. The hot gas side was analyzed using 1-D isentropic flow assumptions, along with heat transfer correlations. The coolant side was evaluated using the hydraulic analysis in the axial direction and the heat transfer analysis in the radial direction. Thermophysical properties and the phase of the coolant were determined using the given property tables and the instantaneous state of the coolant. This flexible and computationally less demanding tool was used to analyze two small-scale engines utilizing liquid hydrocarbon fuels, which are used in modern rocket propulsion. The wall cooling analyses of a liquid oxygen (LOX)/liquid methane (LCH4) engine and a liquid oxygen (LOX)/liquid propane (LC3H8) engine are presented. Fuel and oxidizer were used separately as coolants for both engines, and both of them experienced phase change. Results reveal the advantage of the high mass flow rate of the oxidizer in cooling performance. In addition, the results of this study show that the cooling of the LOX/LC3H8 engine is somewhat more challenging compared to the LOX/LCH4 engine.

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Section: Resultsmentioning

confidence: 99%

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Kose,

Celik

2023

Applied Sciences

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“…The hybrid rocket motor, characterized by a relatively low regression rate, exhibits the capability for long-term operation, which can be applied in sounding rockets, launch vehicle propulsion, and space engines [1][2][3][4]. After the design of the hybrid rocket motor is completed, the expensive firing test is carried out.…”

Section: Introductionmentioning

confidence: 99%

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Meng,

Tian,

Niu

et al. 2024

Aerospace

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Hybrid rocket motors have great development potential due to their outstanding thrust adjustment flexibility and long-term operation ability. However, nozzle erosion during the motor operation can cause an increase in the throat area of the nozzle, which leads to a decrease in combustion chamber pressure and nozzle efficiency. Therefore, a performance prediction model for hybrid rocket motors considering nozzle erosion has become a key technology that must be addressed when developing hybrid rocket motors. This study uses dynamic grid technology to simulate the regression of the combustion surface and nozzle erosion, which fits well with experimental values. The behavior of high-energy particles in the combustion chamber is simulated through a discrete phase model. Notably, distinctive behavior is observed in Al and Mg droplets, with Al droplets exhibiting incomplete vaporization in the combustion chamber while Mg droplets completely vaporize. A ground firing test using the Φ336 mm hybrid rocket motor lasting 200 s is conducted. The results show that the dynamic numerical simulation, accounting for nozzle erosion, substantially enhances performance prediction accuracy. The average deviation in motor thrust remains below 1.8%, and the combustion chamber pressure deviation stays under 2.6%, confirming the precision of the model. Ultimately, both simulation and experimental outcomes indicate a gradual decrease in specific impulse and characteristic velocity over the long-term operation, attributed to the gradual deviation of the oxygen-fuel ratio. This research provides valuable insights for guiding hybrid rocket motor design and optimizing design parameters to improve overall performance. This model can achieve long-duration and high-precision performance predictions for hybrid rocket motors.

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Regenerative cooling in hybrid rocket engines based on Self-Pressurized liquid nitrous oxide

Gallo,

Miyahara,

Kamps

et al. 2024

Applied Thermal Engineering

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One-dimensional modelling of the nozzle cooling with cryogenic oxygen flowing through helical channels in a hybrid rocket

Cited by 7 publications

References 17 publications

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Regenerative Cooling Comparison of LOX/LCH4 and LOX/LC3H8 Rocket Engines Using the One-Dimensional Regenerative Cooling Modelling Tool ODREC

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Regenerative cooling in hybrid rocket engines based on Self-Pressurized liquid nitrous oxide

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