Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine
This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-d...
Ausführliche Beschreibung
Autor*in: |
Denman, Zachary J. [verfasserIn] Wheatley, Vincent [verfasserIn] Smart, Michael K. [verfasserIn] Veeraragavan, Ananthanarayanan [verfasserIn] |
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Format: |
E-Artikel |
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Sprache: |
Englisch |
Erschienen: |
2016 |
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Schlagwörter: |
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Übergeordnetes Werk: |
Enthalten in: Proceedings of the Combustion Institute - Combustion Institute ; ID: gnd/1004025-0, Amsterdam [u.a.] : Elsevier, 2000, 36, Seite 2883-2891 |
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Übergeordnetes Werk: |
volume:36 ; pages:2883-2891 |
DOI / URN: |
10.1016/j.proci.2016.08.081 |
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Katalog-ID: |
ELV001923684 |
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520 | |a This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. | ||
650 | 4 | |a Scramjet | |
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650 | 4 | |a Hydrocarbon | |
650 | 4 | |a Supersonic combustion | |
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700 | 1 | |a Smart, Michael K. |e verfasserin |4 aut | |
700 | 1 | |a Veeraragavan, Ananthanarayanan |e verfasserin |0 (orcid)0000-0001-6810-2204 |4 aut | |
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2016 |
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10.1016/j.proci.2016.08.081 doi (DE-627)ELV001923684 (ELSEVIER)S1540-7489(16)30470-9 DE-627 ger DE-627 rda eng 660 DE-600 Denman, Zachary J. verfasserin aut Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine 2016 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. Scramjet Surrogate fuel Hydrocarbon Supersonic combustion Wheatley, Vincent verfasserin aut Smart, Michael K. verfasserin aut Veeraragavan, Ananthanarayanan verfasserin (orcid)0000-0001-6810-2204 aut Enthalten in Combustion Institute ; ID: gnd/1004025-0 Proceedings of the Combustion Institute Amsterdam [u.a.] : Elsevier, 2000 36, Seite 2883-2891 Online-Ressource (DE-627)495741140 (DE-600)2197968-6 (DE-576)259486582 1873-2704 nnns volume:36 pages:2883-2891 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 AR 36 2883-2891 |
spelling |
10.1016/j.proci.2016.08.081 doi (DE-627)ELV001923684 (ELSEVIER)S1540-7489(16)30470-9 DE-627 ger DE-627 rda eng 660 DE-600 Denman, Zachary J. verfasserin aut Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine 2016 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. Scramjet Surrogate fuel Hydrocarbon Supersonic combustion Wheatley, Vincent verfasserin aut Smart, Michael K. verfasserin aut Veeraragavan, Ananthanarayanan verfasserin (orcid)0000-0001-6810-2204 aut Enthalten in Combustion Institute ; ID: gnd/1004025-0 Proceedings of the Combustion Institute Amsterdam [u.a.] : Elsevier, 2000 36, Seite 2883-2891 Online-Ressource (DE-627)495741140 (DE-600)2197968-6 (DE-576)259486582 1873-2704 nnns volume:36 pages:2883-2891 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 AR 36 2883-2891 |
allfields_unstemmed |
10.1016/j.proci.2016.08.081 doi (DE-627)ELV001923684 (ELSEVIER)S1540-7489(16)30470-9 DE-627 ger DE-627 rda eng 660 DE-600 Denman, Zachary J. verfasserin aut Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine 2016 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. Scramjet Surrogate fuel Hydrocarbon Supersonic combustion Wheatley, Vincent verfasserin aut Smart, Michael K. verfasserin aut Veeraragavan, Ananthanarayanan verfasserin (orcid)0000-0001-6810-2204 aut Enthalten in Combustion Institute ; ID: gnd/1004025-0 Proceedings of the Combustion Institute Amsterdam [u.a.] : Elsevier, 2000 36, Seite 2883-2891 Online-Ressource (DE-627)495741140 (DE-600)2197968-6 (DE-576)259486582 1873-2704 nnns volume:36 pages:2883-2891 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 AR 36 2883-2891 |
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10.1016/j.proci.2016.08.081 doi (DE-627)ELV001923684 (ELSEVIER)S1540-7489(16)30470-9 DE-627 ger DE-627 rda eng 660 DE-600 Denman, Zachary J. verfasserin aut Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine 2016 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. Scramjet Surrogate fuel Hydrocarbon Supersonic combustion Wheatley, Vincent verfasserin aut Smart, Michael K. verfasserin aut Veeraragavan, Ananthanarayanan verfasserin (orcid)0000-0001-6810-2204 aut Enthalten in Combustion Institute ; ID: gnd/1004025-0 Proceedings of the Combustion Institute Amsterdam [u.a.] : Elsevier, 2000 36, Seite 2883-2891 Online-Ressource (DE-627)495741140 (DE-600)2197968-6 (DE-576)259486582 1873-2704 nnns volume:36 pages:2883-2891 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 AR 36 2883-2891 |
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10.1016/j.proci.2016.08.081 doi (DE-627)ELV001923684 (ELSEVIER)S1540-7489(16)30470-9 DE-627 ger DE-627 rda eng 660 DE-600 Denman, Zachary J. verfasserin aut Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine 2016 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. Scramjet Surrogate fuel Hydrocarbon Supersonic combustion Wheatley, Vincent verfasserin aut Smart, Michael K. verfasserin aut Veeraragavan, Ananthanarayanan verfasserin (orcid)0000-0001-6810-2204 aut Enthalten in Combustion Institute ; ID: gnd/1004025-0 Proceedings of the Combustion Institute Amsterdam [u.a.] : Elsevier, 2000 36, Seite 2883-2891 Online-Ressource (DE-627)495741140 (DE-600)2197968-6 (DE-576)259486582 1873-2704 nnns volume:36 pages:2883-2891 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 AR 36 2883-2891 |
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Denman, Zachary J. @@aut@@ Wheatley, Vincent @@aut@@ Smart, Michael K. @@aut@@ Veeraragavan, Ananthanarayanan @@aut@@ |
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Denman, Zachary J. |
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Denman, Zachary J. ddc 660 misc Scramjet misc Surrogate fuel misc Hydrocarbon misc Supersonic combustion Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine |
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Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine |
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Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine |
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supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine |
title_auth |
Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine |
abstract |
This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. |
abstractGer |
This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. |
abstract_unstemmed |
This paper presents the results of a series of shock tunnel experiments of a hydrocarbon-fuelled, Mach 8 shape-transitioning scramjet engine with a cavity combustor. The inlet of the scramjet transitions from a quasi-rectangular capture area to an elliptical throat, which results in a highly three-dimensional flowfield at the combustor entrance. The main focus of the work was to achieve ignition and combustion of hydrocarbon fuels at a high Mach number in a flight-candidate engine that has the necessary three dimensional flow path that is typical of “practical” scramjet engines. The engine was fuelled with a surrogate fuel mixture (64% ethylene and 36% methane by volume) which mimics the extinguishing characteristics of partially cracked JP-7 fuel. Experiments were performed with and without a hydrogen-pilot to demonstrate ignition and combustion. Static pressure measurements throughout the flow path were used in conjunction with experiments where combustion was suppressed, by using nitrogen instead of air as the main flow, to confirm a combustion-induced pressure rise for different injection and piloting strategies. Ignition and supersonic combustion of the surrogate fuel mixture was achieved in all cases where a hydrogen pilot was employed. The pilot hydrogen fuel was injected at the inlet of the engine. Simultaneous injection of the surrogate fuel mixture at the inlet and in the combustor (combined injection) and combustor-only injection did not achieve combustion. |
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Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine |
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