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Atomization and Sprays

Publicou 12 edições por ano

ISSN Imprimir: 1044-5110

ISSN On-line: 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

SHEAR COAXIAL INJECTOR LOX DROPLET MEASUREMENTS AS A FUNCTION OF HYDROGEN INJECTION TEMPERATURE

Volume 18, Edição 1, 2008, pp. 85-96
DOI: 10.1615/AtomizSpr.v18.i1.30
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RESUMO

A hydrogen gas chiller was designed and fabricated in order to simulate the hydrogen temperature ramping test for liquid rocket engines in a single-element gaseous hydrogen/liquid oxygen combustion chamber. Hot fire PDPA measurements of droplet sizes and velocities as a function of the gaseous hydrogen temperature for a fixed mass flow and shear coaxial injector configuration were obtained as the hydrogen temperature was varied from 130 to 290 K, resulting in a doubling of the hydrogen/oxygen velocity and momentum flux ratios. Measured droplet Sauter and arithmetic mean diameters decreased as the hydrogen temperature increased. However, even though the hydrogen temperature change resulted in a doubling of the velocity and momentum flux ratios, the droplet Sauter mean diameter only decreased by 12.5%. These results indicate that the increase in droplet size as the injected hydrogen temperature is decreased may not be a significant contributor to the resulting combustion instability for liquid rocket engines operating at the conditions examined in this study.

CITADO POR
  1. Feng Songjiang, Nie Wansheng, He Bo, Zhuang Fengchen, Control Effects of Baffle on Combustion Instability in a LOX/GH2 Rocket Engine, Journal of Spacecraft and Rockets, 47, 3, 2010. Crossref

  2. Manfletti Chiara, Low Ambient Pressure Injection and Consequences on Ignition of Liquid Rocket Engines, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012. Crossref

  3. Feng Songjiang, Cheng Yufeng, Nie Wansheng, Combustion Instability Analysis in a Hydrogen-Oxygen Rocket Engine, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009. Crossref

  4. Feng Songjiang, Nie Wansheng, A Numerical Study of Oxygen/Hydrogen Mixing and Combustion of a Shear Coaxial Injector, 42nd AIAA Thermophysics Conference, 2011. Crossref

  5. Manfletti Chiara, Laser Ignition of an Experimental Cryogenic Reaction and Control Thruster: Pre-Ignition Conditions, Journal of Propulsion and Power, 30, 4, 2014. Crossref

  6. Gröning Stefan, Hardi Justin, Suslov Dmitry, Oschwald Michael, Influence of hydrogen temperature on the stability of a rocket engine combustor operated with hydrogen and oxygen, CEAS Space Journal, 9, 1, 2017. Crossref

  7. Gröning Stefan, Hardi Justin S., Suslov Dmitry, Oschwald Michael, Injector-Driven Combustion Instabilities in a Hydrogen/Oxygen Rocket Combustor, Journal of Propulsion and Power, 32, 3, 2016. Crossref

  8. Hardi Justin, Oschwald Michael, Dally Bassam B., Study of LOx/H2 Spray Flame Response to Acoustic Excitation in a Rectangular Rocket Combustor, 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013. Crossref

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