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Atomization and Sprays

Published 12 issues per year

ISSN Print: 1044-5110

ISSN Online: 1936-2684

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 1.2 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 1.8 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.3 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00095 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.28 SJR: 0.341 SNIP: 0.536 CiteScore™:: 1.9 H-Index: 57

Indexed in

DROPLET SIZE AND VELOCITY MEASUREMENTS IN A CRYOGENIC JET FLAME OF A ROCKET-TYPE COMBUSTOR USING HIGH-SPEED IMAGING

Volume 26, Issue 5, 2016, pp. 411-438
DOI: 10.1615/AtomizSpr.2015011814
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ABSTRACT

Injectors of cryogenic liquid rocket engines produce large polydisperse and dense sprays due to the pressure and mass flow conditions. Atomization is the dominating process that drives the flame behavior in cryogenic jet flames, when the propellants are injected in subcritical conditions. The main objective of this study is the characterization of a liquid oxygen (LOX) spray in gaseous hydrogen (GH2), in reacting conditions. In the breakup region where liquid particles are not spherical, laser based drop-size techniques suffer from a low validation data rate; thus imaging techniques can be better suited to characterize the spray. High-speed shadowgraphs were used to provide the spray characteristics such as sizes and velocities of the LOX dispersed phase atomized by a GH2 co-flow injected by a shear coaxial injector in a 1 MPa combustion chamber. Cryogenic combustion investigations presented in this paper were carried out on the Mascotte test bench, at Onera. The reacting case was compared qualitatively to a cold flow test, with gaseous He instead of GH2, for which LOX spray shadowgraphs were also recorded. The cold LOX jet was constituted by an envelope of small droplets around the LOX core whereas in the reacting case, those small droplets were not present and bigger liquid structures were revealed, due to vaporization by the flame. Moreover, the difference in terms of gas density between the hot fire and the cold case led to a reduction of the aerodynamic forces which can also explain that droplet velocities, at the injector exit, were higher in the cold case. Velocities of the dispersed phase in reacting conditions were obtained with two different imaging methods, which were applied to the same shadowgraphs: a PTV algorithm and a PIV software, developed at Onera. Both methods agreed well as soon as the droplet density is high enough and they showed that droplet velocities decreased by a factor of 3 in the area investigated. Droplet sizes were measured by image processing in the atomization zone and results were compared with Sauter mean diameters obtained with phase Doppler measurements from the literature. The droplet size is combined with PTV to obtain droplet size/velocity correlations which show that velocity of the smallest droplets decreased more rapidly than velocity of the biggest one, as the axial distance from the injector increased.

CITED BY
  1. Stevenin C., Tomas S., Vallet A., Amielh M., Anselmet F., Flow characteristics of a large-size pressure-atomized spray using DTV, International Journal of Multiphase Flow, 84, 2016. Crossref

  2. Fdida N., Mauriot Y., Vingert L., Ristori A., Théron M., Characterizing primary atomization of cryogenic LOX/Nitrogen and LOX/Helium sprays by visualizations coupled to Phase Doppler Interferometry, Acta Astronautica, 164, 2019. Crossref

  3. Lamanna Grazia, Steinhausen Christoph, Weckenmann Florian, Weigand Bernhard, Bork Benjamin, Preusche Andreas, Dreizler Andreas, Stierle Rolf, Gross Joachim, Laboratory Experiments of High-Pressure Fluid Drops, in High-Pressure Flows for Propulsion Applications, 2020. Crossref

  4. Le Touze C., Dorey L.-H., Rutard N., Murrone A., A compressible two-phase flow framework for Large Eddy Simulations of liquid-propellant rocket engines, Applied Mathematical Modelling, 84, 2020. Crossref

  5. Son Min, Armbruster Wolfgang, Hardi Justin S., Oschwald Michael, Measuring the velocity field of a shear-coaxial, cryogenic flame in a high-pressure rocket thrust chamber, Proceedings of the Combustion Institute, 38, 2, 2021. Crossref

  6. Breitenmoser David, Papadopoulos Petros, Lind Terttaliisa, Prasser Horst-Michael, Droplet size distribution in a full-scale rectangular self-priming Venturi scrubber with liquid film injection, International Journal of Multiphase Flow, 142, 2021. Crossref

  7. Boulal Stéphane, Fdida Nicolas, Matuszewski Lionel, Vingert Lucien, Martin-Benito Miguel, Flame dynamics of a subscale rocket combustor operating with gaseous methane and gaseous, subcritical or transcritical oxygen, Combustion and Flame, 242, 2022. Crossref

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