Liquid Rocket Thrust Chambers

doi:10.2514/4.866760

Cited by 12 publications

(8 citation statements)

References 313 publications

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“…The transition region becomes wider with increasing pressure, but it degenerates to a sharp interface when the pressure decreases to a subcritical value. For p 100 atm, the upper and lower bounds of density for the transition region are 645 and 450 kg∕m 3 , respectively. Figure 5 shows the temporal evolution of the density fields on three different transverse planes along the axial axis from the vortex chamber to the discharge nozzle.…”

Section: Resultsmentioning

confidence: 99%

“…To further explore the underlying flow physics, hydrodynamic waves in the axial and azimuthal directions are analyzed separately. Figure 11 shows the temporal evolution of the density isosurface at ρ 532 kg∕m 3 , located in the interfacial layer between the liquid and gaseous oxygen (see Fig. 2).…”

Section: Flow Instability and Wave Characteristicsmentioning

confidence: 99%

“…S WIRL injectors are widely used in many propulsion and powergeneration systems, including airbreathing engines [1,2] and liquid rockets [3]. The swirling motion induces outward spreading of the liquid film and produces a center toroidal recirculation zone downstream of the injector, thereby significantly improving mixing and combustion efficiency.…”

Section: Introductionmentioning

confidence: 99%

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Comprehensive Study of Cryogenic Fluid Dynamics of Swirl Injectors at Supercritical Conditions

et al. 2017

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A comprehensive study is conducted to enhance the understanding of swirl injector flow dynamics at supercritical conditions. The formulation is based on full-conservation laws and accommodates real-fluid thermodynamics and transport theories over the entire range of fluid states of concern. Liquid oxygen at 120 K is injected into a supercritical oxygen environment at 300-600 K. Detailed three-dimensional flow structures are visualized for the first time in the pressure range of 100-200 atm. A smooth fluid transition from the compressed-liquid to light-gas state occurs, which is in contrast to a distinct interface of phase change at subcritical pressure. Dynamic behaviors of the oscillatory flowfield are explored using the spectral analysis and proper orthogonal decomposition technique. Various underlying mechanisms dictating flow evolution, including shear-layer, helical, centrifugal, and acoustic instabilities, are studied in depth. The hydrodynamic wave motions in the liquid-oxygen film are found to propagate in two different modes: one along the axial direction at the local wave speed; the other in the azimuthal direction and convected downstream at the mean flow velocity. Results show good agreement with the analytical prediction of the overall response transfer function of the swirl injector. The dominant mode of the azimuthal wave is triggered by the natural acoustic oscillation within the injector. Compared with the two-dimensional axisymmetric results, the calculated liquid-oxygen film is thicker and the spreading angle smaller due to the momentum loss and vortical dynamics in the azimuthal direction.

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Section: Resultsmentioning

confidence: 99%

Section: Flow Instability and Wave Characteristicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Comprehensive Study of Cryogenic Fluid Dynamics of Swirl Injectors at Supercritical Conditions

et al. 2017

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“…Introduction S WIRL injectors are widely used to achieve efficient mixing and combustion in propulsion and power-generation systems, including airbreathing engines [1,2] and liquid rockets [3]. The swirling motion of the injected fluid can improve flame stability by producing toroidal recirculation zones and reduce combustion length by inducing high rates of entrainment of the ambient fluid and fast mixing [4].…”

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confidence: 99%

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Wang

Yang

2017

Journal of Propulsion and Power

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The mixing and combustion characteristics of liquid-oxygen/kerosene bi-swirl injectors are investigated under the supercritical conditions typical of contemporary rocket engines. The basis of the study is a large-eddy simulation technique combined with a unified treatment of real-fluid thermodynamics. The turbulence/chemistry interaction is treated using a laminar flamelet library approach. Emphasis is placed on the near-field flow and flame development downstream of the inner swirler. The flame is found to be stabilized by two counter-rotating vortices in the wake region of the liquid-oxygen post, which is covered by the kerosene-rich mixture. The width of the kerosene annulus is found to significantly affect the injector behavior. A wider annulus induces a larger spreading angle of the liquidoxygen stream, which intercepts the kerosene stream in a more efficient way. Increasing the annulus width, however, imposes a wake region in a broader zone. The resultant flame becomes relatively unstable if the flame thickness is larger than the liquid-oxygen post thickness. Variation of the kerosene annulus width has a negligible effect on the dominant frequency of the pressure fluctuation, but it changes the amplitude of fluctuation.

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“…Mills et al 68 reported that, due to the nature of hypergolic propellants, low activation energies are involved, which leads to the formation of many complex intermediates. Interestingly, ammonium nitrate formed only during steady-state operation.…”

Section: Preignition and Preignition Productsmentioning

confidence: 99%

Propellant Ignition and Flame Propagation

2004

Liquid Rocket Thrust Chambers

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Nomenclature AB = Arrhenius preexponentials C = concentration c p = heat capacity d q = quenching distance E -activation energy Emin = minimum ignition energy F = fuel h = heat k = conductivity / = liquid m -reaction order with respect to fuel TV = total order of reaction n = reaction order with respect to oxidizer O = oxidizer o = initial condition or totalThe ratio of this ignition pressure to the nominal pressure is then given byThis expression should not be taken as exact. It provides only an estimate of the ignition overpressure and indicates that a longer delay r t will induce a higher pressure peak. To reduce the amplitude of this pressure, one has to decrease the delay and inject the propellants progressively into the chamber. Purchased from American Institute of Aeronautics and Astronautics Downloaded by PENNSYLVANIA STATE UNIVERSITY on March 15, 2015 | http://arc.aiaa.org |

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Liquid Rocket Thrust Chambers

Abstract: Downloaded by PURDUE UNIVERSITY on July 27, 2015 | http://arc.aiaa.org |

Cited by 12 publications

References 313 publications

Comprehensive Study of Cryogenic Fluid Dynamics of Swirl Injectors at Supercritical Conditions

Comprehensive Study of Cryogenic Fluid Dynamics of Swirl Injectors at Supercritical Conditions

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Propellant Ignition and Flame Propagation

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