Numerical study on the combustion characteristics of a fuel-centered pintle injector for methane rocket engines

Son, Min; Radhakrishnan, Kanmaniraja; Yoon, Youngbin; Koo, Jaye

doi:10.1016/j.actaastro.2017.02.005

Cited by 65 publications

(12 citation statements)

References 26 publications

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“…Under the influence of the large recirculation zones between combustor walls and combustor axis in Figure 7, the premixed fuel gas continues to flow along the pintle wall with the same axial velocity after leaving the axial injection channel. The hemispherical shape of the pintle tip results into a local high-pressure zone with small axial velocity near the pintle tip, which is significantly different from that of the previous two-dimensional simulations [29,39]. The large recirculation zones and local high-pressure zone cause throttling area reduction when the premixed fuel gas approaches the pintle tip.…”

contrasting

confidence: 59%

Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine

Jin

Shen

Zhou

et al. 2020

International Journal of Aerospace Engineering

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LOX/GCH4 pintle injector is suitable for variable-thrust liquid rocket engines. In order to provide a reference for the later design and experiments, three-dimensional numerical simulations with the Euler-Lagrange method were performed to study the effect of the initial particle diameter on the combustion characteristics of a LOX/GCH4 pintle rocket engine. Numerical results show that, as the momentum ratio between the radial LOX jet and the axial gas jet is 0.033, the angle between the LOX particle trace and the combustor axial is very small. Due to the large recirculation zones, premixed combustion mainly occurs in the injector wake region. As the initial LOX particle diameter increases, the LOX evaporation rate and the combustion efficiency decrease until the combustion terminates with the initial LOX particle diameter greater than 110 μm. The oscillation amplitude of the combustor pressure increases significantly along with the increase of the initial LOX particle diameter, and the low-frequency unstable combustion occurs when the initial LOX particle diameter exceeds 60 μm. The combustor pressure oscillation at about 40 Hz couples with the swinging process of spray and flame, while the unsteady LOX evaporation amplifies the combustor pressure oscillations at 80 Hz and its harmonic frequency.

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contrasting

confidence: 59%

Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine

Jin

Shen

Zhou

et al. 2020

International Journal of Aerospace Engineering

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“…13 With the increasing demand for cryogenic, nontoxic, and low-carbon propellants, liquid oxygen/liquid methane (LOX/LCH 4 ) propellants have aroused the interest of many countries for a bipropellant propulsion system. [14][15][16] Compared with conventional propellant combinations, LOX/LCH 4 propellants have the advantage of high-density specific impulse, super maneuverability, and convenience for manufacture. 17 However, on account of the physical properties of the methane, the density and specific heat of methane will have dramatic changes on account of the transcritical flow behavior in cooling channels even with small variations in temperature and pressure.…”

Section: Introductionmentioning

confidence: 99%

Throttling simulation and control of liquid oxygen/liquid methane rocket engine pressurized by the electric pump

Hu,

Wu,

Liang

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part I:

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This article presented simulation and control of a liquid oxygen/liquid methane variable thrust rocket engine pressurized by the electric pump in the throttling process. To get a proper injection pressure drop, the variation of the injection area was investigated and determined. In the control scheme, the combustion pressure and mixture ratio were the targets. To simplify the control scheme, the pressure and mixture ratio were correlated to the oxygen mass flow rate and methane mass flow rate, respectively. By controlling the propellant mass flow rate, the target engine thrust was reached. In addition, the influence of mass flow rate measurement points on the control effect was analyzed. The simulation results showed that the designed controller can reduce the overshoot of the critical engine parameters. Therefore, the maximum temperature of the thrust chamber wall after the regenerative cooling was decreased. Consequently, the thrust control errors were within 3% except for the points where the thrust changed suddenly, which can meet the mission requirements.

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“…With the increasing demand for cryogenic, nontoxic, and low-carbon propellants, LOX/LCH4 propellants become preferable for a biopropellant propulsion system due to their favorable characteristics for long life and reusability. 1,2 Liquid methane presents several opportunities for launchers, such as less-constrained design thanks to the soft-cryo temperature, easier safety conditions for reusable trajectories, and better operability. 3 The electric pump gained more attention in recent years with the development of batteries and electric motors, 4,5 especially after the launch of the Electron rocket with the Rutherford engine pressurized by an electric pump.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Pipeline fault simulation and control of a liquid rocket engine

Cheng

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The feedback control system was designed to control the pipeline blockage and leakage fault. Based on the open-loop engine system, different degrees of faults were simulated, and the changes in system parameters when faults occur were analyzed. Then, the faults were injected into the engine system with feedback control, and the effects of the controller to different degrees of faults and the changes of the parameters of the electric pump with the controller were studied. The simulation results showed that under the action of the feedback control system, the deviation of the engine system parameters caused by these faults can recover to the set value within a few seconds. When the fault disappears, the system parameters can be still within the normal operating range.

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Numerical study on the combustion characteristics of a fuel-centered pintle injector for methane rocket engines

Cited by 65 publications

References 26 publications

Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine

Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine

Throttling simulation and control of liquid oxygen/liquid methane rocket engine pressurized by the electric pump

Pipeline fault simulation and control of a liquid rocket engine

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