Student-Faculty Research on the Combustion in Hybrid-Propellant Rocket Engine for Aerospace Specialization in Mechanical Engineering Curriculum

Naoumov, Viatcheslav; Haralambous, Alexander; Goldreich, Adam; Boynton, Thomas; Koç, Murat

doi:10.2514/6.2012-436

Cited by 5 publications

(1 citation statement)

References 7 publications

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“…In order to perform long-term research on the combustion of bio-derived fuels and fuels with additives and obtain regression rates, a lab-scale HPRE test fixture was designed, built, and fabricated in 2010 by a group of Mechanical Engineering students at Central Connecticut State University [15][16][17][18][19] (Fig.4). The engine itself consists of a mixing chamber, a combustion chamber with an inner tube to house the solid propellant grain, and a conical graphite nozzle assembly.…”

Section: Test Apparatus For the Research Of Combustion Of Bio-dermentioning

confidence: 99%

Undergraduate Research on Peculiarities of the Combustion of Ecologically Clean Paraffin Wax Fuels in Hybrid Propellant Rocket Engines

Naoumov

Masoud

Skomin

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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The paper describes the student-faculty research of the combustion of non-conventional bio-derived fuels in a lab-scale Hybrid Propellant Rocket Engine (HPRE). The long-term goal of the senior capstone project is to study specific features of combustion of nonconventional bio-derived hybrid propellant rocket fuels such as paraffin, beeswax, and lard, which are non-toxic and non-explosive with different oxidizers. Combustion of above fuels with additives (aluminum powder) was studied as well. The study was concentrated on the obtaining of regression rates (velocities of the combustion) for the listed propellants, and investigating losses of melted unburned bio-derived fuels. Such fuels could replace conventional toxic and explosive fuels, and are planned to be used on the NASA sounding rockets. A lab-scale HPRE, test fixture and instrumentation system have been designed, manufactured, assembled and used for the research and analysis of combustion. More than 60 tests were performed to study the specific features of combustion using paraffin and bee's wax. The results of the study were presented at 51 st AIAA Meeting and Exhibits, and SciTech, 52 nd Aerospace Sciences Meeting. This paper summarizes 2013/14 research results on the combustion of paraffin and paraffin with aluminum powder; represents new findings, such as regression rate formulas for paraffin wax combustion with 10% of aluminum powder obtained for two different diameters of the grain ports; the paper also illuminates the study of the losses of unburned paraffin wax and discusses novel methodology of the prediction of losses of unburned fuel based on the measurements of the temperature of the exhaust plum of combustion products. Nomenclature T-Thrust, N e u -Velocity of combustion products at nozzle exit, m/s e A -Exit area of the nozzle, m 2 e p -Pressure at the exit of the nozzle, Pa P -Pressure in the combustion chamber, psig a p -Ambient pressure, Pa k -Mass oxidizer-to-fuel ratio st k -Stoichiometric mass oxidizer-to-fuel ratio 1 Professor, 2 Figure 1. Simplified diagram of HPRE Figure 2. Simplified schematic of the combustion in HPRE 2 R -Gas constant sp I -Specific impulse m/s or s f m  -Mass flow rate of fuel, kg/s ox m  -Mass flow rate of oxidizer, kg/s p m  -Mass flow rate of propellant, kg/s f G -Average mass flux of fuel through the grain port, g/cm 2 s ox G -Average mass flux of oxidizer through the grain port, g/cm 2 s p G -Average mass flux of propellant through the grain port, g/cm 2 s i A -Cross-sectional area of injector, m 2 a -Jet coefficient m u -Velocity on the axis of the plume of the combustion products, m/s  r -Regression rate, mm/s in d -Initial port diameter (before fuel burnout), cm fin d -Final port diameter (after fuel burnout), cm * A -Nozzle throat area, m 2  -Specific heat ratio

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Section: Test Apparatus For the Research Of Combustion Of Bio-dermentioning

confidence: 99%

Undergraduate Research on Peculiarities of the Combustion of Ecologically Clean Paraffin Wax Fuels in Hybrid Propellant Rocket Engines

Naoumov

Masoud

Skomin

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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Hybrid Propellant Rocket Engine Test Fixture and Research on the Combustion of Non-Conventional Fuels

Naoumov

Haralambous

Goldreich

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper introduces the first step of the research performed by the Central Connecticut State University faculty/student research team on the combustion of nonconventional fuels in a small-scale Hybrid Propellant Rocket Engine (HPRE). The long-term goal of the research was to investigate the combustion of non-conventional bio-derived fuels such as beeswax, lard, with different oxidizers (oxygen, hydrogen peroxide, nitrous oxide) along with additives such as aluminum powder; and to obtain approximation formulas for the calculation of regression rates for listed propellants and propellants with additives. A small-scale HPRE, test fixture and instrumentation system have been designed, manufactured and assembled. To validate proper operation of the engine, test facility and instrumentation system, the first tests focused primarily on the combustion of paraffin and bee's wax with oxygen. Initial experiments were performed; experimental data were collected and followed by comparison with theoretical data, calculated using computer code, created by authors. The approximation formulas for the calculation of the regression rates of the paraffin with oxygen were obtained and compared with existing data of other researchers. Nomenclature T-Thrust, N e u -Velocity of combustion products at nozzle exit, m/s e A -Exit area of the nozzle, m 2 e p -Pressure at the exit of the nozzle, pa P -Pressure in the combustion chamber, psig a p -Ambient pressure, pa  -Molar oxidizer-to-fuel ratio K -Mass oxidizer-to-fuel ratio st K -Stoichiometric mass oxidizer-to-fuel ratio i b -Number of atoms of an element, , in a chemical compound i  -Valence of an element, i in a chemical compound j  -Molar mass of chemical compound, j, kg/kmol f m  -Mass flow rate of fuel, kg/s ox m  -Mass flow rate of oxidizer, kg/s 1 Professor,

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Senior Capstone Design Project for Aerospace Specialization and Student-Faculty Research on Propulsion

Naoumov

Al-Masoud

Haralambous

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Student-Faculty Research on the Combustion in Hybrid-Propellant Rocket Engine for Aerospace Specialization in Mechanical Engineering Curriculum

Cited by 5 publications

References 7 publications

Undergraduate Research on Peculiarities of the Combustion of Ecologically Clean Paraffin Wax Fuels in Hybrid Propellant Rocket Engines

Undergraduate Research on Peculiarities of the Combustion of Ecologically Clean Paraffin Wax Fuels in Hybrid Propellant Rocket Engines

Hybrid Propellant Rocket Engine Test Fixture and Research on the Combustion of Non-Conventional Fuels

Senior Capstone Design Project for Aerospace Specialization and Student-Faculty Research on Propulsion

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