Optimization of a flight-worthy scramjet combustor through CFD

Manna, P.; Dharavath, Malsur; Sinha, P. P.; Chakraborty, Debasis

doi:10.1016/j.ast.2012.07.005

Cited by 73 publications

(20 citation statements)

References 15 publications

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“…Simulations were carried out by varying the grids starting from 20.34 mm to 2.159 mm with varying minimum grid size and the results are found to be independent of grid size as can be seen in the centre line pressure distribution along the nozzle axis presented in Fig 3.Grid convergence or discretisation error, which is the error of the solution of the different equations compared to the exact solution of the partial differential equation, is the major source of numerical error. Introduced by Roache 21 , the formulation was used by Aswin and Chakraborty 22 and Manna 23 , et al to estimate the error for the problems of sonic jet injection into supersonic cross-stream and scramjet combustor flow-field simulation, respectively.…”

Section: Results and Discussion 31 Single-phase Calculation Of Titamentioning

confidence: 99%

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Chaturvedi¹,

Kumar²,

Chakraborty³

2015

DSJ

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Section: Results and Discussion 31 Single-phase Calculation Of Titamentioning

confidence: 99%

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Chaturvedi¹,

Kumar²,

Chakraborty³

2015

DSJ

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“…For the present calculation, p 2 with h 2 ∕h 1 2, and GCI is on the order of ε. The same GCI-based error estimate has already been used by the authors in analyzing various reacting and nonreacting flows [14,24]. The maximum error between two simulations is within 5% with maximum deviation in the region where fuel injection struts are placed.…”

Section: Angle Of Attack Equal To Zero Degreesmentioning

confidence: 95%

“…The scramjet combustor configuration was changed in several iterations [11][12][13] to meet the requirement of the hypersonic vehicle. A number of ground tests in connected pipe mode tests [12,13] and numerical simulations [14,15] were carried out to finalize the number of struts, their positions, and fuel injection locations to have a benign thermal environment and optimum performance of the flight-sized engine.…”

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confidence: 99%

Computational Fluid Dynamics Simulation of Tip-to-Tail for Hypersonic Test Vehicle

Dharavath

Manna

Chakraborty

2015

Journal of Propulsion and Power

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Computational fluid dynamics simulations are carried out for a complete hypersonic vehicle integrating both external (nonreacting) and internal (reacting) flow together to calculate the scramjet combustor performance and vehicle net thrust minus drag. Simulations are carried out for a flight Mach number of about six. Three-dimensional Navier-Stokes equations are solved along with the shear stress transport k-ω turbulence model and single-step chemical reaction based on fast chemistry. The Lagrangian particle tracking method for droplets is used for combustion of kerosene fuel. Flow is largely nonuniform at the inlet of the combustor. Mass flow of ingested air increases with increase in angle of attack. Because of more combustion of fuel, wall surface pressure is higher for α 6 deg compared with α 0 deg. Combustion efficiency and thrust achieved are found to increase with the increase in angle of attack. Considerable amount of thrust is obtained from a single expansion ram nozzle and achievement of positive thrust-drag for the whole vehicle is demonstrated. The computational analysis of the whole vehicle provides net forces and moments of the whole vehicle, which is very useful for the mission analysis of the vehicle. NomenclatureA ebu , B ebu = model coefficient of eddy dissipation model D = Rosin Rammler diameter F = blending function, factor of safety in grid convergence index, thrust f = parameter of grid convergence index H = enthalpy, altitude h = height of cruise vehicle, grid spacing I = species component, specific impulse i, j, k = three axes direction k = turbulent kinetic energy M = molecular weight, Mach number m = flow rate P = pressure Pr = Prandtl number p = order of accuracy in grid convergence index q = heat flux R k = mixing rate of eddy dissipation model S = source term T = temperature t = time x, y, z = three axes direction Y = species mass fraction α = angle of attack η = efficiency μ = viscosity ν = dispersion factor, stoichiometric coefficient, kinematic viscosity ρ = density τ = shear stress ϕ = equivalence ratio Ω = strain rate ω = turbulent frequency Subscripts a = air ci = combustor inlet CV = cruise vehicle f = fuel i = various species k = x, y, z directions L = lift o = oxidizer p = product rec = recovery SERN = single expansion ramp nozzle t = turbulent 0 = total 1, 2 = fine, coarse grid ∞ = freestream

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“…A mesh size of 1.2 mm is sufficient to obtain grid independent results with approximately 3.6 million grid points. The grid convergence is calculated based on the Gird Convergence Index (GCI) criteria (Manna et al, 2013;Reddy, 2013). If the GCI for two successive grid sizes is below 3%, it can be considered that grid convergence has been achieved (Manna et al, 2013).…”

Section: Grid Generation and Grid Independencementioning

confidence: 99%

“…The grid convergence is calculated based on the Gird Convergence Index (GCI) criteria (Manna et al, 2013;Reddy, 2013). If the GCI for two successive grid sizes is below 3%, it can be considered that grid convergence has been achieved (Manna et al, 2013). GCI details for different grid sizes are reported in Table 2.…”

Section: Grid Generation and Grid Independencementioning

confidence: 99%

Investigations on Emission Characteristics of Liquid Fuels in a Swirl Combustor

Reddy

Trivedi

Sawant

et al. 2014

Combustion Science and Technology

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Flameless combustion is an effective method to suppress CO and NO X emissions from combustion systems with improved combustion efficiency. Flameless combustion is achieved through simultaneous preheating and dilution of fresh reactants with internal recirculation of hot combustion products leading to a distributed reaction zone and uniform temperature distribution throughout the volume of the combustor. In the present study, a high-intensity swirl-based combustor operating with liquid fuel in a flameless combustion mode is developed for industrial applications and designed to run at atmospheric pressure conditions. Detailed investigations on the emission characteristics for various operating conditions in flameless combustion mode have been reported. The experiments have been carried out for a range of heat release rates varying from 5 to 10 MW/m 3 . Swirl flow pattern is achieved through tangential air injection to enhance the internal recirculation of hot combustion products into fresh reactants. Preliminary numerical studies aimed at understanding flow pattern in four different combustor configurations show that recirculation rate increases with an increase in the divergence angle of the combustor. This helps achieve flameless combustion mode. Recirculation rate increases with a decrease in the outlet diameter from 80 mm to 25 mm. Based on the degree of the combustion completeness, extended frustum of the cone-based configuration (60 • ) has been proposed to obtain low emission combustion mode with liquid fuels. Temperature distribution and emissions are measured and compared for different thermal inputs (heat release intensities) and air-preheat temperatures. Measurements of acoustic, CO, and NO X emissions show that these emissions are reduced by an order of magnitude when the combustor is operated in flameless combustion mode as compared to conventional combustion mode.

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Optimization of a flight-worthy scramjet combustor through CFD

Cited by 73 publications

References 15 publications

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Computational Fluid Dynamics Simulation of Tip-to-Tail for Hypersonic Test Vehicle

Investigations on Emission Characteristics of Liquid Fuels in a Swirl Combustor

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