LOx Jet Atomization Under Transverse Acoustic Oscillations

Hardi, Justin; Martinez, Harvey Camilo Gomez; Oschwald, Michael; Dally, Bassam B.

doi:10.2514/1.b34979

Cited by 53 publications

(33 citation statements)

References 9 publications

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“…These are presented here for comparison with the previous measurements made by the authors [24,25] under 1T-mode excitation. Table 1 lists the complete range of operating conditions covered for all 1T and 1L1T measurements.…”

Section: Intact Core Lengthsupporting

confidence: 61%

“…The core breakup mechanism has changed from its natural axial shedding mode to the one of stripping and entrainment in the oscillating transverse §ow. Again, this behavior is described in more detail in [24,25].…”

Section: Without Acoustic Excitationmentioning

confidence: 99%

“…The breakup mechanism is one of successive detachments of large, dense oxygen structures which become entrained in the axial mean §ow. A detailed description of this natural shedding behavior, as well as example image sequences, can be found in [24,25]. Figure 7 shows example frames during 1T-mode excitation in 60-bar GH 2 test C. Here, the central LOx core length is greatly reduced compared to its natural state, now only extending around 7L/D downstream of injection.…”

Section: Without Acoustic Excitationmentioning

confidence: 99%

“…Measurements of the intact core length with increasing transverse acoustic amplitude were presented by Hardi et al [24,25]. The measurements were made in a 2D multielement LOx/H 2 combustor with optical access and siren forcing, known as ¢BKH.£ High-speed images show signi¦cant reduction in core length during excitation of the 1T mode of the combustion chamber.…”

mentioning

confidence: 99%

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Cryogenic oxygen jet response to transverse acoustic excitation with the first transverse and the first combined longitudinal-transverse modes

Hardi

Oschwald

2016

Progress in Propulsion Physics

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The intact length of the dense oxygen core from an oxygen hydrogen shear coaxial rocket injector was measured. The measurements were made in a rectangular rocket combustor with optical access and acoustic forcing. The combustor was operated at chamber pressures of 40 and 60 bar, with either ambient temperature or cryogenic hydrogen. The multielement injection spray is subjected to forced transverse gas oscillations of two di¨erent acoustic resonance modes; the ¦rst transverse (1T) mode at 4200 Hz and the ¦rst combined longitudinal-transverse (1L1T) at 5500 Hz. Intact core length is measured from high-speed shadowgraph imaging. The dependence of intact core length with increasing acoustic amplitude is compared for the two modes of excitation.

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Section: Intact Core Lengthsupporting

confidence: 61%

Section: Without Acoustic Excitationmentioning

confidence: 99%

Section: Without Acoustic Excitationmentioning

confidence: 99%

mentioning

confidence: 99%

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Cryogenic oxygen jet response to transverse acoustic excitation with the first transverse and the first combined longitudinal-transverse modes

Hardi

Oschwald

2016

Progress in Propulsion Physics

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“…This is exemplified in a book edited by Yang and Anderson [3] , in the monograph written by Culick [12] and in many further investigations. In the recent period, many studies pursue the analytical modeling of the driving mechanisms as for example [13][14][15][16][17][18][19] while new model scale experiments and scaling methods are reported in [20][21][22][23][24][25][26][27][28][29][30][31] . These experiments have provided novel information on the interaction between the combustion region and acoustic modes with much attention focused on transverse modes which are only weakly damped in thrust chambers and are consequently the most dangerous (the detrimental effect of transverse modes was already well recognized during the early period [11,32] ).…”

Section: Introductionmentioning

confidence: 99%

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Urbano

Selle

Staffelbach

et al. 2016

Combustion and Flame

177

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et al.. Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector Liquid Rocket Engine. Combustion and Flame, Elsevier, 2016, 169, pp. a b s t r a c tThis article explores the possibility of analyzing combustion instabilities in liquid rocket engines by making use of Large Eddy Simulations (LES). Calculations are carried out for a complete small-scale rocket engine, including the injection manifold thrust chamber and nozzle outlet. The engine comprises 42 coaxial injectors feeding the combustion chamber with gaseous hydrogen and liquid oxygen and it operates at supercritical pressures with a maximum thermal power of 80 MW. The objective of the study is to predict the occurrence of transverse high-frequency combustion instabilities by comparing two operating points featuring different levels of acoustic activity. The LES compares favorably with the experiment for the stable load point and exhibits a nonlinearly unstable transverse mode for the experimentally unstable operating condition. A detailed analysis of the instability retrieves the experimental data in terms of spectral features. It is also found that modifications of the flame structures and of the global combustion region configuration have similarities with those observed in recent model scale experiments. It is shown that the overall acoustic activity mainly results from the combination of one transverse and one radial mode of the chamber, which are also strongly coupled with the oxidizer injectors.

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Characterisation of acoustic energy content in an experimental combustion chamber with and without external forcing

2015

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LOx Jet Atomization Under Transverse Acoustic Oscillations

Cited by 53 publications

References 9 publications

Cryogenic oxygen jet response to transverse acoustic excitation with the first transverse and the first combined longitudinal-transverse modes

Cryogenic oxygen jet response to transverse acoustic excitation with the first transverse and the first combined longitudinal-transverse modes

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Characterisation of acoustic energy content in an experimental combustion chamber with and without external forcing

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