Ethylene Flame Dynamics and Inlet Unstart in a Model Scramjet
Ethylene flame dynamics in a model scramjet installed in an open test section of an arc-heated hypersonic wind tunnel are experimentally investigated with freestreams of Mach 4.5–9. An ethylene fuel jet is injected into the model scramjet that is autoignited by high-enthalpy flows compressed and dec...
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| Veröffentlicht in: | Journal of propulsion and power 2014-11, Vol.30 (6), p.1577-1585 |
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| container_title | Journal of propulsion and power |
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| creator | Liu, Qili Passaro, Andrea Baccarella, Damiano Do, Hyungrok |
| description | Ethylene flame dynamics in a model scramjet installed in an open test section of an arc-heated hypersonic wind tunnel are experimentally investigated with freestreams of Mach 4.5–9. An ethylene fuel jet is injected into the model scramjet that is autoignited by high-enthalpy flows compressed and decelerated by a train of shock waves and boundary layers developing in the scramjet isolator/combustor. The ethylene flame behavior is captured by a high-speed movie camera through optical access windows on the model and characterized by surface pressure/temperature traces recorded at five different locations along the flowpath through the model scramjet. Downstream pressure buildup due to combustion heat release, shock-induced compression, and mass loading via the fuel jet triggers the flame propagation toward upstream, stabilizes the flame at a location in the combustor, or pushes the flame further upstream to cause inlet unstart. In particular, flame dynamics while the scramjet undergoes the inlet unstart with Mach 4.5 freestreams are investigated intensively. In addition, stagnation temperature, overall fuel concentration, and oxygen concentration in freestream flows are varied to investigate their influences on the flame dynamics. The flame propagates faster and anchors further upstream with increased total temperature, oxygen enrichment, and overall equivalence ratio slightly above unity. |
| doi_str_mv | 10.2514/1.B35214 |
| format | Article |
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An ethylene fuel jet is injected into the model scramjet that is autoignited by high-enthalpy flows compressed and decelerated by a train of shock waves and boundary layers developing in the scramjet isolator/combustor. The ethylene flame behavior is captured by a high-speed movie camera through optical access windows on the model and characterized by surface pressure/temperature traces recorded at five different locations along the flowpath through the model scramjet. Downstream pressure buildup due to combustion heat release, shock-induced compression, and mass loading via the fuel jet triggers the flame propagation toward upstream, stabilizes the flame at a location in the combustor, or pushes the flame further upstream to cause inlet unstart. In particular, flame dynamics while the scramjet undergoes the inlet unstart with Mach 4.5 freestreams are investigated intensively. In addition, stagnation temperature, overall fuel concentration, and oxygen concentration in freestream flows are varied to investigate their influences on the flame dynamics. The flame propagates faster and anchors further upstream with increased total temperature, oxygen enrichment, and overall equivalence ratio slightly above unity.</description><identifier>ISSN: 0748-4658</identifier><identifier>EISSN: 1533-3876</identifier><identifier>DOI: 10.2514/1.B35214</identifier><identifier>CODEN: JPPOEL</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Arc heating ; Boundary layers ; Combustion chambers ; Construction ; Deceleration ; Dynamic tests ; Dynamics ; Enthalpy ; Equivalence ratio ; Ethylene ; Flame propagation ; Fuels ; Hypersonic wind tunnels ; Inlets ; Oxygen enrichment ; Pressure ; Scramjets ; Shock waves ; Stagnation temperature ; Supersonic combustion ramjet engines ; Unstart (engines) ; Upstream</subject><ispartof>Journal of propulsion and power, 2014-11, Vol.30 (6), p.1577-1585</ispartof><rights>Copyright © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code and $10.00 in correspondence with the CCC.</rights><rights>Copyright © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 1533-3876/14 and $10.00 in correspondence with the CCC.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a385t-ae3078feda3a3edfda2cd915220f50b9561dfc13dbdeed00a51259a0367369903</citedby><cites>FETCH-LOGICAL-a385t-ae3078feda3a3edfda2cd915220f50b9561dfc13dbdeed00a51259a0367369903</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><creatorcontrib>Liu, Qili</creatorcontrib><creatorcontrib>Passaro, Andrea</creatorcontrib><creatorcontrib>Baccarella, Damiano</creatorcontrib><creatorcontrib>Do, Hyungrok</creatorcontrib><title>Ethylene Flame Dynamics and Inlet Unstart in a Model Scramjet</title><title>Journal of propulsion and power</title><description>Ethylene flame dynamics in a model scramjet installed in an open test section of an arc-heated hypersonic wind tunnel are experimentally investigated with freestreams of Mach 4.5–9. An ethylene fuel jet is injected into the model scramjet that is autoignited by high-enthalpy flows compressed and decelerated by a train of shock waves and boundary layers developing in the scramjet isolator/combustor. The ethylene flame behavior is captured by a high-speed movie camera through optical access windows on the model and characterized by surface pressure/temperature traces recorded at five different locations along the flowpath through the model scramjet. Downstream pressure buildup due to combustion heat release, shock-induced compression, and mass loading via the fuel jet triggers the flame propagation toward upstream, stabilizes the flame at a location in the combustor, or pushes the flame further upstream to cause inlet unstart. In particular, flame dynamics while the scramjet undergoes the inlet unstart with Mach 4.5 freestreams are investigated intensively. In addition, stagnation temperature, overall fuel concentration, and oxygen concentration in freestream flows are varied to investigate their influences on the flame dynamics. The flame propagates faster and anchors further upstream with increased total temperature, oxygen enrichment, and overall equivalence ratio slightly above unity.</description><subject>Arc heating</subject><subject>Boundary layers</subject><subject>Combustion chambers</subject><subject>Construction</subject><subject>Deceleration</subject><subject>Dynamic tests</subject><subject>Dynamics</subject><subject>Enthalpy</subject><subject>Equivalence ratio</subject><subject>Ethylene</subject><subject>Flame propagation</subject><subject>Fuels</subject><subject>Hypersonic wind tunnels</subject><subject>Inlets</subject><subject>Oxygen enrichment</subject><subject>Pressure</subject><subject>Scramjets</subject><subject>Shock waves</subject><subject>Stagnation temperature</subject><subject>Supersonic combustion ramjet engines</subject><subject>Unstart (engines)</subject><subject>Upstream</subject><issn>0748-4658</issn><issn>1533-3876</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2014</creationdate><recordtype>article</recordtype><recordid>eNp90EFLAzEQBeAgCtYq-BMCInjZmkk2yebgQWurhYoH7TlMN1ncsputyfbQf2-lgtKDp7l8vDc8Qi6BjbiE_BZGD0JyyI_IAKQQmSi0OiYDpvMiy5UsTslZSivGQBVKD8jdpP_YNj54Om2w9fRxG7Cty0QxODoLje_pIqQeY0_rQJG-dM439K2M2K58f05OKmySv_i5Q7KYTt7Hz9n89Wk2vp9nKArZZ-gF00XlHQoU3lUOeekMSM5ZJdnSSAWuKkG4pfPeMYYSuDTIhNJCGcPEkNzsc9ex-9z41Nu2TqVvGgy-2yQLSoOUkmmzo1cHdNVtYth9Z3luhNRSM_mfAgU5CJEb_ltbxi6l6Cu7jnWLcWuB2e-1Ldj92jt6vadYI_4JO3Rfa8F5pQ</recordid><startdate>20141101</startdate><enddate>20141101</enddate><creator>Liu, Qili</creator><creator>Passaro, Andrea</creator><creator>Baccarella, Damiano</creator><creator>Do, Hyungrok</creator><general>American Institute of Aeronautics and Astronautics</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20141101</creationdate><title>Ethylene Flame Dynamics and Inlet Unstart in a Model Scramjet</title><author>Liu, Qili ; Passaro, Andrea ; Baccarella, Damiano ; Do, Hyungrok</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a385t-ae3078feda3a3edfda2cd915220f50b9561dfc13dbdeed00a51259a0367369903</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2014</creationdate><topic>Arc heating</topic><topic>Boundary layers</topic><topic>Combustion chambers</topic><topic>Construction</topic><topic>Deceleration</topic><topic>Dynamic tests</topic><topic>Dynamics</topic><topic>Enthalpy</topic><topic>Equivalence ratio</topic><topic>Ethylene</topic><topic>Flame propagation</topic><topic>Fuels</topic><topic>Hypersonic wind tunnels</topic><topic>Inlets</topic><topic>Oxygen enrichment</topic><topic>Pressure</topic><topic>Scramjets</topic><topic>Shock waves</topic><topic>Stagnation temperature</topic><topic>Supersonic combustion ramjet engines</topic><topic>Unstart (engines)</topic><topic>Upstream</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Liu, Qili</creatorcontrib><creatorcontrib>Passaro, Andrea</creatorcontrib><creatorcontrib>Baccarella, Damiano</creatorcontrib><creatorcontrib>Do, Hyungrok</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Journal of propulsion and power</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Liu, Qili</au><au>Passaro, Andrea</au><au>Baccarella, Damiano</au><au>Do, Hyungrok</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Ethylene Flame Dynamics and Inlet Unstart in a Model Scramjet</atitle><jtitle>Journal of propulsion and power</jtitle><date>2014-11-01</date><risdate>2014</risdate><volume>30</volume><issue>6</issue><spage>1577</spage><epage>1585</epage><pages>1577-1585</pages><issn>0748-4658</issn><eissn>1533-3876</eissn><coden>JPPOEL</coden><abstract>Ethylene flame dynamics in a model scramjet installed in an open test section of an arc-heated hypersonic wind tunnel are experimentally investigated with freestreams of Mach 4.5–9. An ethylene fuel jet is injected into the model scramjet that is autoignited by high-enthalpy flows compressed and decelerated by a train of shock waves and boundary layers developing in the scramjet isolator/combustor. The ethylene flame behavior is captured by a high-speed movie camera through optical access windows on the model and characterized by surface pressure/temperature traces recorded at five different locations along the flowpath through the model scramjet. Downstream pressure buildup due to combustion heat release, shock-induced compression, and mass loading via the fuel jet triggers the flame propagation toward upstream, stabilizes the flame at a location in the combustor, or pushes the flame further upstream to cause inlet unstart. In particular, flame dynamics while the scramjet undergoes the inlet unstart with Mach 4.5 freestreams are investigated intensively. In addition, stagnation temperature, overall fuel concentration, and oxygen concentration in freestream flows are varied to investigate their influences on the flame dynamics. The flame propagates faster and anchors further upstream with increased total temperature, oxygen enrichment, and overall equivalence ratio slightly above unity.</abstract><cop>Reston</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.B35214</doi><tpages>9</tpages></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 0748-4658 |
| ispartof | Journal of propulsion and power, 2014-11, Vol.30 (6), p.1577-1585 |
| issn | 0748-4658 1533-3876 |
| language | eng |
| recordid | cdi_crossref_primary_10_2514_1_B35214 |
| source | Alma/SFX Local Collection |
| subjects | Arc heating Boundary layers Combustion chambers Construction Deceleration Dynamic tests Dynamics Enthalpy Equivalence ratio Ethylene Flame propagation Fuels Hypersonic wind tunnels Inlets Oxygen enrichment Pressure Scramjets Shock waves Stagnation temperature Supersonic combustion ramjet engines Unstart (engines) Upstream |
| title | Ethylene Flame Dynamics and Inlet Unstart in a Model Scramjet |
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