Formation mechanism of high-frequency combustion oscillations in a model rocket engine combustor

We study the formation mechanism of high-frequency combustion oscillations in a model rocket combustor from the viewpoints of symbolic dynamics and complex networks. The flow velocity fluctuations in the fuel injector generated by the pressure fluctuations in the combustor give rise to the periodic...

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Veröffentlicht in:	Physics of fluids (1994) 2021-06, Vol.33 (6)
Hauptverfasser:	Shima, Satomi, Nakamura, Kosuke, Gotoda, Hiroshi, Ohmichi, Yuya, Matsuyama, Shingo
Format:	Artikel
Sprache:	eng
Schlagworte:	Combustion chambers Flow velocity Fluid dynamics Fuel injection Heat release rate Oscillations Oxidizing agents Physics Rocket engines
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container_title	Physics of fluids (1994)
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creator	Shima, Satomi Nakamura, Kosuke Gotoda, Hiroshi Ohmichi, Yuya Matsuyama, Shingo
description	We study the formation mechanism of high-frequency combustion oscillations in a model rocket combustor from the viewpoints of symbolic dynamics and complex networks. The flow velocity fluctuations in the fuel injector generated by the pressure fluctuations in the combustor give rise to the periodic ignition of the unburnt fuel/oxidizer mixture, resulting in a significant change in the heat release rate fluctuations in the combustor. The heat release rate fluctuations drive the pressure fluctuations in the combustor before a transition state, while the pressure fluctuations in the combustor gradually begin to significantly affect the heat release rate fluctuations during the transition to combustion oscillations. The directional feedback process during the transition and subsequent combustion oscillations is identified by the directionality index of the symbolic transfer entropy. The thermoacoustic power network enables us to understand the physical mechanism behind the transition and subsequent combustion oscillations.
doi_str_mv	10.1063/5.0048785
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The flow velocity fluctuations in the fuel injector generated by the pressure fluctuations in the combustor give rise to the periodic ignition of the unburnt fuel/oxidizer mixture, resulting in a significant change in the heat release rate fluctuations in the combustor. The heat release rate fluctuations drive the pressure fluctuations in the combustor before a transition state, while the pressure fluctuations in the combustor gradually begin to significantly affect the heat release rate fluctuations during the transition to combustion oscillations. The directional feedback process during the transition and subsequent combustion oscillations is identified by the directionality index of the symbolic transfer entropy. 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The thermoacoustic power network enables us to understand the physical mechanism behind the transition and subsequent combustion oscillations.</description><subject>Combustion chambers</subject><subject>Flow velocity</subject><subject>Fluid dynamics</subject><subject>Fuel injection</subject><subject>Heat release rate</subject><subject>Oscillations</subject><subject>Oxidizing agents</subject><subject>Physics</subject><subject>Rocket engines</subject><issn>1070-6631</issn><issn>1089-7666</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2021</creationdate><recordtype>article</recordtype><recordid>eNp9kEtPwzAQhC0EEqVw4B9Y4gRSih_xI0dUUUCqxAXOJnHs1iWxi50g9d-TPoADEqfdwzezOwPAJUYTjDi9ZROEcikkOwIjjGSRCc758XYXKOOc4lNwltIKIUQLwkfgbRZiW3YueNgavSy9Sy0MFi7dYpnZaD564_UG6tBWfdphIWnXNDtJgs7DErahNg2MQb-bDhq_cN58C0I8Bye2bJK5OMwxeJ3dv0wfs_nzw9P0bp7pnIouo6youcbECiG1LXJW46rmjGBtqbC1EYWwHOfC4kpbwrCxRBApcWExpRUSdAyu9r7rGIanU6dWoY9-OKkIy6mUlAg2UNd7SseQUjRWraNry7hRGKltgYqpQ4EDe7Nnh8DdLu8P_BniL6jWtf0P_uv8Ba01f5w</recordid><startdate>20210601</startdate><enddate>20210601</enddate><creator>Shima, Satomi</creator><creator>Nakamura, Kosuke</creator><creator>Gotoda, Hiroshi</creator><creator>Ohmichi, Yuya</creator><creator>Matsuyama, Shingo</creator><general>American Institute of Physics</general><scope>AJDQP</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>8FD</scope><scope>H8D</scope><scope>L7M</scope><orcidid>https://orcid.org/0000-0002-0812-1267</orcidid><orcidid>https://orcid.org/0000-0001-6402-8510</orcidid></search><sort><creationdate>20210601</creationdate><title>Formation mechanism of high-frequency combustion oscillations in a model rocket engine combustor</title><author>Shima, Satomi ; Nakamura, Kosuke ; Gotoda, Hiroshi ; Ohmichi, Yuya ; Matsuyama, Shingo</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c437t-359d6c12f778cf945d1bd6521cf37fde797f6147f1bcf251ef2728819f133b073</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2021</creationdate><topic>Combustion chambers</topic><topic>Flow velocity</topic><topic>Fluid dynamics</topic><topic>Fuel injection</topic><topic>Heat release rate</topic><topic>Oscillations</topic><topic>Oxidizing agents</topic><topic>Physics</topic><topic>Rocket engines</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Shima, Satomi</creatorcontrib><creatorcontrib>Nakamura, Kosuke</creatorcontrib><creatorcontrib>Gotoda, Hiroshi</creatorcontrib><creatorcontrib>Ohmichi, Yuya</creatorcontrib><creatorcontrib>Matsuyama, Shingo</creatorcontrib><collection>AIP Open Access Journals</collection><collection>CrossRef</collection><collection>Technology Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Physics of fluids (1994)</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Shima, Satomi</au><au>Nakamura, Kosuke</au><au>Gotoda, Hiroshi</au><au>Ohmichi, Yuya</au><au>Matsuyama, Shingo</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Formation mechanism of high-frequency combustion oscillations in a model rocket engine combustor</atitle><jtitle>Physics of fluids (1994)</jtitle><date>2021-06-01</date><risdate>2021</risdate><volume>33</volume><issue>6</issue><issn>1070-6631</issn><eissn>1089-7666</eissn><coden>PHFLE6</coden><abstract>We study the formation mechanism of high-frequency combustion oscillations in a model rocket combustor from the viewpoints of symbolic dynamics and complex networks. 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source	AIP Journals Complete; Alma/SFX Local Collection
subjects	Combustion chambers Flow velocity Fluid dynamics Fuel injection Heat release rate Oscillations Oxidizing agents Physics Rocket engines
title	Formation mechanism of high-frequency combustion oscillations in a model rocket engine combustor
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