Computational Simulation of Axis Symmetric Aft Wall Angle Cavity in Supersonic Flow Field

Relangi, Naresh; Garimella, Divyasri; Jayaraman, K.; Venkatesan, Jayakumar; Jeyakumar, S.; Ingenito, Antonella

doi:10.2514/6.2020-3712

Cited by 6 publications

(5 citation statements)

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“…This validation has been performed for non-reacting flows since experimental data are available only for cold flow conditions. Figure 3 shows the comparison of the wall static pressure for the four different geometries: a good agreement among computational and test bench results 33 has found. Numerical simulations of the reacting flow have been performed for the same 4 combustor configurations to suggest the best geometry for supersonic combustion chambers based on aft wall inclined cavities.…”

Section: Grid Convergence Analysis and Validation Of Resultsmentioning

confidence: 54%

“…To validate the numerical results, a comparison with experimental data 32 for the same inlet conditions 33 has been done. This validation has been performed for non-reacting flows since experimental data are available only for cold flow conditions.…”

Section: Grid Convergence Analysis and Validation Of Resultsmentioning

confidence: 99%

“…The addition of heat also decreases the Mach number till the thermal chocking, this is why a divergent angle of 3° has been considered. Numerical results show that the addition of the heat to the supersonic flow due to fuel-air reaction employs around 40% of pressure losses and bow shocks, shock-supersonic stream interaction have contributed the remaining 17% 33 to the overall pressure losses. The lowest total pressure increase due to the heat addition is found for the no-cavity configuration.…”

Section: Numerical Resultsmentioning

confidence: 99%

See 2 more Smart Citations

The investigation of inclined AFT wall cavities in a circular scramjet combustor

Relangi

Ingenito

Jeyakumar

2022

International Journal of Engine Research

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Achieving good mixing with high combustion efficiency, stable flame holding, and low stagnation pressure losses are still open issues in supersonic reacting flows. Mixing and vorticity in supersonic flows are mainly driven by the baroclinic term that is correlated to the density and pressure gradients. An increase of the baroclinic term has been observed to strongly depend on shock waves arising within the combustion chamber. This work numerically investigated the interaction between the fuel jet and the air stream as a function of the aft wall angle inclination. In fact, this parameter has a primary impact on the shock wave inclination arising from the cavity leading edge and therefore on the baroclinic term. Four different combustor geometries have been investigated: without cavity and with three different aft wall inclinations (90°–15°, 60°–15°, 30°–15°). 3D RANS numerical simulations showed that the primary ramp angle has a critical impact on the fuel-air mixing and consequently on the combustion efficiency. A correlation between the combustor geometry and the shock angle inclination has been proposed. Greater combustion efficiency, homogeneous H2O, and temperature distribution across the combustor are found with the 30–15 aft wall cavity configuration. Lowering the primary aft wall of the cavity from 90° to 30°, resulted in the rising of a stronger bow shock, extended recirculation volume within the cavity, and increased fuel-air mixing.

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Section: Grid Convergence Analysis and Validation Of Resultsmentioning

confidence: 54%

Section: Grid Convergence Analysis and Validation Of Resultsmentioning

confidence: 99%

Section: Numerical Resultsmentioning

confidence: 99%

See 1 more Smart Citation

The investigation of inclined AFT wall cavities in a circular scramjet combustor

Relangi

Ingenito

Jeyakumar

2022

International Journal of Engine Research

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“…To solve the RANS equations, Ansys Fluent commercial code with a density-based solver and the SST K-Omega turbulence model is used. Non-reacting flow numerical investigations have been validated against experimental bench results [28].…”

Section: Computational Analysis On Circular Combustormentioning

confidence: 99%

Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR)

Relangi

Peri

Domingos

et al. 2022

IOP Conf. Ser.: Mater. Sci. Eng.

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The paper deals with the design of a two-stage to orbit rocket launcher loaded with a solid rocket booster, scramjet, and hybrid rocket for delivering a 100kg payload in 200 km circular orbit. The possibility of implementing a cavity-based axisymmetric circular combustor in a scramjet is proposed. Computational analysis on various injector locations in a circular combustor and their validation with the test bench results were performed. The utilisation of a hybrid rocket in the final stage of the launcher to deliver the payload is discussed and the performance characteristics of the circular scramjet combustor and the hybrid rocket are shown. The overall mission proposed based on the sustainable and reusable characteristics.

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“…Since only non-reacting experiments are performed in Reference [33], the validation of numerical simulations with experimental data has been carried out for similar conditions [35]. The wall static pressures along the flow direction and the momentum distribution at the exit of the combustor in the radial direction of the flow are compared.…”

Section: Validationmentioning

confidence: 99%

The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor

2021

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This paper presents the effect of cavity-based injection in an axisymmetric supersonic combustor using numerical investigation. An axisymmetric cavity-based angled and transverse injections in a circular scramjet combustor are studied. A three-dimensional Reynolds-averaged Navier–Stokes (RANS) equation along with the k-ω shear-stress transport (SST) turbulence model and species transport equations are considered for the reacting flow studies. The numerical results of the non-reacting flow studies are validated with the available experimental data and are in good agreement with it. The performance of the injection system is analyzed based on the parameters like wall pressures, combustion efficiency, and total pressure loss of the scramjet combustor. The transverse injection upstream of the cavity and at the bottom wall of the cavity in a supersonic flow field creates a strong shock train in the cavity region that enhances complete combustion of hydrogen-air in the cavity region compared to the cavity fore wall injection schemes. Eventually, the shock train in the flow field enhances the total pressure loss across the combustor. However, a marginal variation in the total pressure loss is observed between the injection schemes.

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Computational Simulation of Axis Symmetric Aft Wall Angle Cavity in Supersonic Flow Field

Cited by 6 publications

References 0 publications

The investigation of inclined AFT wall cavities in a circular scramjet combustor

The investigation of inclined AFT wall cavities in a circular scramjet combustor

Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR)

The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor

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