Experimental Investigation of Ramburner Performance. Part I. Liquid Propellant Runs
This report describes the results of a series of connected-pipe runs with an air-augmented rocket system burning liquid rocket propellants. The liquid propellant runs served to evaluate the behavior of the facility and instrumentation with regard to accuracy and to provide performance data for combu...
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description | This report describes the results of a series of connected-pipe runs with an air-augmented rocket system burning liquid rocket propellants. The liquid propellant runs served to evaluate the behavior of the facility and instrumentation with regard to accuracy and to provide performance data for combustion where the chemical rate processes were relatively fast compared with those of metal combustion. The ramburner was designed to provide axisymmetric, coaxial mixing of the primary and secondary streams in a constant area duct. No mixing aids were employed. Nitrogen tetroxide and Aerozine-50 served as the rocket propellants. The secondary air was preheated by combustion to a nominal temperature of 1100 R to simulate flight stagnation conditions. Runs were made with nominal pressures in the ramburner of 90 and 175 psia. The air/propellant ratio was varied from 5 to 13 (approximately 250 to 600 percent theoretical air). Two oxidizer-to-fuel ratios were employed for the primary rocket: 0.8 (fuel rich) and 2.0 (stoichiometric). Combustion efficiencies between 75 and 90 percent were observed for the complete system, decreasing with increasing air/propellant ratio. Estimated uncertainties in the efficiency values were + or - 3 percent. Ramburner efficiencies tended to be 10 to 15 percent lower and were subject to uncertainties in the neighborhood of + or - 6 percent. A slight decrease in efficiency with decreasing pressure was also observed. (Author)
See also Part 2, AD-523 198. |
format | Report |
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See also Part 2, AD-523 198.</description><language>eng</language><subject>AEROZINE 50 ; AIR AUGMENTATION ; CAPTIVE TESTS ; COMBUSTION ; COMBUSTION CHAMBERS ; COMPUTER PROGRAMS ; COMPUTERIZED SIMULATION ; DUCTED ROCKETS ; EFFICIENCY ; FLUID FLOW ; HYDRAZINES ; INTERIOR BALLISTICS ; Liquid Propellant Rocket Engines ; LIQUID ROCKET PROPELLANTS ; METHYL HYDRAZINES ; NITROGEN COMPOUNDS ; NITROGEN OXIDE(N2O4) ; NITROGEN OXIDES ; PERFORMANCE(ENGINEERING) ; ROCKET NOZZLES ; SECONDARY COMBUSTION ; SIMULATION ; STAGNATION POINT ; SUBROUTINES ; TETROXIDES ; THERMOCHEMISTRY ; THERMODYNAMICS ; THRUST AUGMENTATION</subject><creationdate>1972</creationdate><rights>APPROVED FOR PUBLIC RELEASE</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27567,27568</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0907377$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Meese, R A</creatorcontrib><creatorcontrib>Skifstad, J G</creatorcontrib><creatorcontrib>PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER</creatorcontrib><title>Experimental Investigation of Ramburner Performance. Part I. Liquid Propellant Runs</title><description>This report describes the results of a series of connected-pipe runs with an air-augmented rocket system burning liquid rocket propellants. The liquid propellant runs served to evaluate the behavior of the facility and instrumentation with regard to accuracy and to provide performance data for combustion where the chemical rate processes were relatively fast compared with those of metal combustion. The ramburner was designed to provide axisymmetric, coaxial mixing of the primary and secondary streams in a constant area duct. No mixing aids were employed. Nitrogen tetroxide and Aerozine-50 served as the rocket propellants. The secondary air was preheated by combustion to a nominal temperature of 1100 R to simulate flight stagnation conditions. Runs were made with nominal pressures in the ramburner of 90 and 175 psia. The air/propellant ratio was varied from 5 to 13 (approximately 250 to 600 percent theoretical air). Two oxidizer-to-fuel ratios were employed for the primary rocket: 0.8 (fuel rich) and 2.0 (stoichiometric). Combustion efficiencies between 75 and 90 percent were observed for the complete system, decreasing with increasing air/propellant ratio. Estimated uncertainties in the efficiency values were + or - 3 percent. Ramburner efficiencies tended to be 10 to 15 percent lower and were subject to uncertainties in the neighborhood of + or - 6 percent. A slight decrease in efficiency with decreasing pressure was also observed. (Author)
See also Part 2, AD-523 198.</description><subject>AEROZINE 50</subject><subject>AIR AUGMENTATION</subject><subject>CAPTIVE TESTS</subject><subject>COMBUSTION</subject><subject>COMBUSTION CHAMBERS</subject><subject>COMPUTER PROGRAMS</subject><subject>COMPUTERIZED SIMULATION</subject><subject>DUCTED ROCKETS</subject><subject>EFFICIENCY</subject><subject>FLUID FLOW</subject><subject>HYDRAZINES</subject><subject>INTERIOR BALLISTICS</subject><subject>Liquid Propellant Rocket Engines</subject><subject>LIQUID ROCKET PROPELLANTS</subject><subject>METHYL HYDRAZINES</subject><subject>NITROGEN COMPOUNDS</subject><subject>NITROGEN OXIDE(N2O4)</subject><subject>NITROGEN OXIDES</subject><subject>PERFORMANCE(ENGINEERING)</subject><subject>ROCKET NOZZLES</subject><subject>SECONDARY COMBUSTION</subject><subject>SIMULATION</subject><subject>STAGNATION POINT</subject><subject>SUBROUTINES</subject><subject>TETROXIDES</subject><subject>THERMOCHEMISTRY</subject><subject>THERMODYNAMICS</subject><subject>THRUST AUGMENTATION</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1972</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFzLEKwkAMgOEuDqK-gUNewFLoUBylViw4lOpeYpuTwF2upqn4-Dq4O_3DB_8yuVbvkZQDiaGHWl40GT_QOApEBy2G-6xCCg2pixpQekqhQTWoU7jwc-YBGo0jeY9i0M4yrZOFQz_R5tdVsj1Vt_K8G4z77vsXsu5wzPZZkRdF_oc_E9U1Kg</recordid><startdate>19720731</startdate><enddate>19720731</enddate><creator>Meese, R A</creator><creator>Skifstad, J G</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>19720731</creationdate><title>Experimental Investigation of Ramburner Performance. Part I. Liquid Propellant Runs</title><author>Meese, R A ; Skifstad, J G</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD09073773</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1972</creationdate><topic>AEROZINE 50</topic><topic>AIR AUGMENTATION</topic><topic>CAPTIVE TESTS</topic><topic>COMBUSTION</topic><topic>COMBUSTION CHAMBERS</topic><topic>COMPUTER PROGRAMS</topic><topic>COMPUTERIZED SIMULATION</topic><topic>DUCTED ROCKETS</topic><topic>EFFICIENCY</topic><topic>FLUID FLOW</topic><topic>HYDRAZINES</topic><topic>INTERIOR BALLISTICS</topic><topic>Liquid Propellant Rocket Engines</topic><topic>LIQUID ROCKET PROPELLANTS</topic><topic>METHYL HYDRAZINES</topic><topic>NITROGEN COMPOUNDS</topic><topic>NITROGEN OXIDE(N2O4)</topic><topic>NITROGEN OXIDES</topic><topic>PERFORMANCE(ENGINEERING)</topic><topic>ROCKET NOZZLES</topic><topic>SECONDARY COMBUSTION</topic><topic>SIMULATION</topic><topic>STAGNATION POINT</topic><topic>SUBROUTINES</topic><topic>TETROXIDES</topic><topic>THERMOCHEMISTRY</topic><topic>THERMODYNAMICS</topic><topic>THRUST AUGMENTATION</topic><toplevel>online_resources</toplevel><creatorcontrib>Meese, R A</creatorcontrib><creatorcontrib>Skifstad, J G</creatorcontrib><creatorcontrib>PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Meese, R A</au><au>Skifstad, J G</au><aucorp>PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Experimental Investigation of Ramburner Performance. Part I. Liquid Propellant Runs</btitle><date>1972-07-31</date><risdate>1972</risdate><abstract>This report describes the results of a series of connected-pipe runs with an air-augmented rocket system burning liquid rocket propellants. The liquid propellant runs served to evaluate the behavior of the facility and instrumentation with regard to accuracy and to provide performance data for combustion where the chemical rate processes were relatively fast compared with those of metal combustion. The ramburner was designed to provide axisymmetric, coaxial mixing of the primary and secondary streams in a constant area duct. No mixing aids were employed. Nitrogen tetroxide and Aerozine-50 served as the rocket propellants. The secondary air was preheated by combustion to a nominal temperature of 1100 R to simulate flight stagnation conditions. Runs were made with nominal pressures in the ramburner of 90 and 175 psia. The air/propellant ratio was varied from 5 to 13 (approximately 250 to 600 percent theoretical air). Two oxidizer-to-fuel ratios were employed for the primary rocket: 0.8 (fuel rich) and 2.0 (stoichiometric). Combustion efficiencies between 75 and 90 percent were observed for the complete system, decreasing with increasing air/propellant ratio. Estimated uncertainties in the efficiency values were + or - 3 percent. Ramburner efficiencies tended to be 10 to 15 percent lower and were subject to uncertainties in the neighborhood of + or - 6 percent. A slight decrease in efficiency with decreasing pressure was also observed. (Author)
See also Part 2, AD-523 198.</abstract><oa>free_for_read</oa></addata></record> |
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source | DTIC Technical Reports |
subjects | AEROZINE 50 AIR AUGMENTATION CAPTIVE TESTS COMBUSTION COMBUSTION CHAMBERS COMPUTER PROGRAMS COMPUTERIZED SIMULATION DUCTED ROCKETS EFFICIENCY FLUID FLOW HYDRAZINES INTERIOR BALLISTICS Liquid Propellant Rocket Engines LIQUID ROCKET PROPELLANTS METHYL HYDRAZINES NITROGEN COMPOUNDS NITROGEN OXIDE(N2O4) NITROGEN OXIDES PERFORMANCE(ENGINEERING) ROCKET NOZZLES SECONDARY COMBUSTION SIMULATION STAGNATION POINT SUBROUTINES TETROXIDES THERMOCHEMISTRY THERMODYNAMICS THRUST AUGMENTATION |
title | Experimental Investigation of Ramburner Performance. Part I. Liquid Propellant Runs |
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