Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics

Soni, Rahul Kumar; De, Ashoke

doi:10.1007/s12206-017-0215-0

Cited by 45 publications

(12 citation statements)

References 30 publications

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“…Reflected shock is formed before the throat of the inlet which interacts with the shear layer to form vortices. This leads to fuel jet break up and aids in near field mixing [18]. Shock formed are converged at a point and then reflected, which strikes in front of the throat.…”

Section: Results and Analysismentioning

confidence: 99%

Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7

Darlami¹,

Bhandari²,

Pandey³

et al. 2020

AJMA

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The incomplete mixing of fuel and the drag induced in the engine are the main problems encountered in scramjets.Proper mixing of fuel can be achieved if the fuel is injected from the inlet of the engine. The fluid domain of Busemann Inlet at Mach 7 with boundary layer fuel injection using slot injectors along the wall was simulated with hydrogen fuel. Static pressure ratio at throat and inlet, along with Mach number at the throat were the design parameters of the Busemann inlet. Hydrogen fuel injection at two different equivalence ratios (0.3 and 0.7) was simulated successively at a temperature of 100 K and Mach 2.5. The state of mixing was studied for three different injection angles (30°, 45°, and 60°) for different equivalence ratios. The injection angles do not have a substantial effect on the hydrogen fuel mixing with the mainstream flow for equivalence ratio 0.3 Whereas, the dispersion of fuel increases as the increase in injection angles for equivalence ratio 0.7. But the total pressure recovery is maintained to the design value for equivalence ratio 0.3 rather than 0.7. Similarly, 45° fuel injection maintains a higher total pressure recovery than in other injection angles of 30° and 60°. Injection technique other than slot injection can be used to study further the effect of fuel mixing in Busemann Inlet.

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Section: Results and Analysismentioning

confidence: 99%

Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7

Darlami¹,

Bhandari²,

Pandey³

et al. 2020

AJMA

View full text Add to dashboard Cite

show abstract

“…The appropriate governing equations (1) to (5) describing the continuity equation, Navier‐Stokes equation, and combustion model, for fluid flow are written as follows 21,22,34,35 :…”

Section: Physical Model Simulation Methodology and Validation Of Comentioning

confidence: 99%

Aerodynamic investigation of the shock train in a scramjet with the effects of backpressure and divergent angles

Gugulothu

2020

Heat Trans

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Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of a shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify the two-dimensional Reynolds-averaged Navier-Stokes equation with the compressible fluid flow by considering the densitybased solver with the standard k-ε turbulence model. The species transport model with a single-step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in the open literature. The obtained results show that the variation of the divergence angle and backpressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the backpressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also move towards the leading edge of the isolator leading to a rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced backpressures.

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“…The appropriate governing Eqs. (1)-(5) describing the continuity equation, Navier Stokes equation and combustion model for fluid flow is written as [21,22,28,29].…”

Section: Simulation Methodologymentioning

confidence: 99%

Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles

Gugulothu¹,

Bhaskar²,

Babu³

2020

Numerical and Experimental Studies on Combustion Engines and Vehicles

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Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures.

show abstract

Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics

Cited by 45 publications

References 30 publications

Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7

Study and Analysis of Fuel Injection at Busemann Inlet at Mach 7

Aerodynamic investigation of the shock train in a scramjet with the effects of backpressure and divergent angles

Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles

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