Mixing, chemical reaction and flow field development in ducted rockets

Vanka, Surya Pratap; Craig, R. R.; Stull, F. D.

doi:10.2514/6.1985-1271

Cited by 23 publications

(13 citation statements)

References 6 publications

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“…To simplify the problem, the flow is considered to be steadystate in mean, and the wall boundary is considered to be adiabatic. 7) The turbulent flux (Reynolds) equations of conservation of mass, momentum, stagnation enthalpy and chemical species may all be taken in the common form:…”

Section: Gas Flow Computationmentioning

confidence: 99%

“…Specific details about the equations may be found in Ref. 7). Even though the fast-chemistry model contains many important aspects of diffusion flames, finite-rate reactions based on multi-step mechanisms must be taken into account if more information is desired concerning detailed flow structures and heat-release distribution.…”

Section: Gas Flow Computationmentioning

confidence: 99%

“…1) Previous investigations relevant to the ducted rocket secondary combustor have been performed by several research groups. [4][5][6][7][8] Chuang et al 4) studied the flowfield in a twodimensional ducted rocket combustor with glass windows employing laser light-sheet for flow visualization and a laser doppler velocimeter (LDV) for velocity measurement. This work showed that the ducted rocket secondary combustor flowfield pattern depends strongly on the mass flux of the ram air and the momentum ratio of ram air to fuel-rich gas.…”

Section: Introductionmentioning

confidence: 99%

“…It was shown that for inlet angles Ó 2013 The Japan Society for Aeronautical and Space Sciences greater than 60 deg, the geometries intrinsically direct a significant portion of the inlet flow towards the dome head region without the need for diverter devices. Vanka et al 7) solved the three-dimensional reacting flow equations with combustion processes modeled by a one-step chemical reaction scheme. Detailed flow structure, fuel dispersal patterns and temperature fields were calculated for a ducted rocket with two side inlets.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Investigation and Numerical Simulation of Secondary Combustor Flow in Boron-Based Propellant Ducted Rocket

Xia

Wang

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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This paper establishes a two-phase reacting flow model in the secondary combustor of a ducted rocket. The threedimensional Favre-averaged compressible turbulent N-S equations are used as the governing equations of the reacting flow, the improved k $ " two-equation turbulence model is used to simulate the turbulent flow, and the eddy break up model is used to simulate the gas combustion. The particle-phase solution is obtained using a well-established boron particle ignition and combustion model. Boron particles are ejected from the exit of the gas generator into a secondary combustor and their trajectories are traced through the reacting flowfield using discrete phase models. The secondary combustion in a cylindrical combustor for the ducted rocket is investigated preliminarily with tests conducted on a connected-pipe ramjet test bed. During the test, boron-based fuel-rich HTPB propellant is used. The effect of factors, such as air/fuel ratio, velocity of air injection and dome height on the performance of the combustor and the engine is examined. The work described in this paper represents an attempt to direct the design of the secondary chamber in order to increase combustion efficiency. The experimental results show that the reacting flow model established in this paper is correct.

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Section: Gas Flow Computationmentioning

confidence: 99%

Section: Gas Flow Computationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Experimental Investigation and Numerical Simulation of Secondary Combustor Flow in Boron-Based Propellant Ducted Rocket

Xia

Wang

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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“…Their work has established qualitatively the importance of several geometric and aerodynamic parameters for the specific impulse of the system. Vanka et al 9 solved the three-dimensional reacting flow equations with combustion processes modeled by a one-step, fast chemical reaction scheme. The detailed flow structures, fuel dispersal patterns, and temperature field were calculated for a typical ducted rocket configuration with two side inlets.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of turbulent reacting flows in solid-propellant ducted rocket combustors

Cherng

Yang

Kuo

1989

Journal of Propulsion and Power

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A theoretical model has been developed to investigate turbulent mixing and combustion processes in the main combustion chamber of a solid-propellant ducted rocket. The formulation is based on Favre-averaged conservation equations with a two-step chemical reaction scheme and is solved by a semi-implicit finite-difference method. Turbulence closure is achieved using a well-known k-e two-equation model. Calculated flow structures show good agreement with preliminary experimental results obtained from the schlieren flow-visualization study. The influences of various parameters, including dome height and inlet flow angle, on the propulsive performance of the system are investigated in detail. Nomenclature-constants in combustion model Q, C 2 , C M = const ants in turbulence model E\, E 2 = activation energies / = mixture fraction G k = production term in Eq. (9) H = stagnation enthalpy H c = half-height of combustor H d = dome height Hj = distance from fuel-rich injector to combustor wall / sp = specific impulse k = turbulence kinetic energy Pr = Prandtl number Pr t = turbulent Prandtl number p = pressure R u = universal gas constant S = reaction rate, defined in Eq. (16) $$ = source term in Eq. (17) Sc = Schmidt number Sc t = turbulent Schmidt number T = temperature u = axial velocity U T = friction velocity V = velocity vector v = vertical velocity W -molecular weight w a = width of air inlet port uy = width of gas-generator injector port x -axial coordinate Y =mass fraction y -vertical coordinate = dimensionless distance from the wall, Ok>0t Diacriticals Subscripts a / ft* i = turbulent transport coefficient in Eq. (17) = heat of formation = turbulent energy dissipation rate = conserved scalar = inlet flow angle = dynamic viscosity = effective viscosity = turbulent viscosity = density = flow varaible in Eq. (17) = production rate of species = constants in turbulence model = time-averaged quantity = Favre-averaged (mass-weighted) quantity = value at inlet/combustor interface = value at gas-generator exit port = fuel = species

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Theoretical investigation of combustion characteristics in ram‐jet dump combustor with side‐inlet

Chuang

Lin

Chen

et al. 1992

Numerical Methods in Fluids

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SUMMARYThe combustion flow of a sudden-expansioin dump combustor with injecting side-inlet is analysed using the SIMPLE-C algorithm and the Jones-Launder k-c two-equation turbulence model. The transport properties of velocity, turbulence kinetic energy, temperature and combustion efficiency as a function of the injected mass fraction and the number of side-inlet nozzles are solved in this paper. The axial velocities of the sudden-expansion dump combustor without injected side-inlet flow are solved first and found to be in good agreement with the experimental data of Moon and Rudinger. For a fixed value of the side-inlet number the wall temperature and combustion efficiency of the dump combustor are decreased when the injected mass fraction is increased. For a fixed value of the injected mass fraction the wall temperature and combustion efficiency are decreased when the number of side-inlet nozzles is increased.

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Mixing, chemical reaction and flow field development in ducted rockets

Cited by 23 publications

References 6 publications

Experimental Investigation and Numerical Simulation of Secondary Combustor Flow in Boron-Based Propellant Ducted Rocket

Experimental Investigation and Numerical Simulation of Secondary Combustor Flow in Boron-Based Propellant Ducted Rocket

Numerical study of turbulent reacting flows in solid-propellant ducted rocket combustors

Theoretical investigation of combustion characteristics in ram‐jet dump combustor with side‐inlet

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