Effect of parametric variation of strut layout and position on the performance of a typical two-strut based scramjet combustor

Choubey, Gautam; Pandey, Krishna Murari

doi:10.1016/j.ijhydene.2017.03.014

Cited by 114 publications

(15 citation statements)

References 49 publications

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“…The model is characterized by robustness, economy, and reasonable accuracy for a wide range of turbulent flows. It was previously [20][21][22]25,32 reported that the SST k-ω turbulence model provides a better prediction of flow features having combustion and high-speed flows. The transport equation of the SST k-ω model is based on the turbulent kinetic energy (k) and specific rate of dissipation (ω) as given below:…”

Section: Turbulence Modelmentioning

confidence: 99%

“…A comprehensive study of different strut configurations and fuel injection locations has been conducted. [20][21][22][23][24] It was observed that in order to reduce the pressure loss in the combustion and enhance efficiency, it was necessary to augment and accelerate the mixing between the air and the fuel. Two half-angled strut configuration was tested and with different attack angles and found that configuration at zero attack angle had better combustion and maximum peak temperature in comparison to configuration with attack angle -3 and 3 , and a single strut.…”

Section: Introductionmentioning

confidence: 99%

“…It was also seen that the assumption of higher boundary layer thickness at the inlet of the combustion chamber had a negative impact on the prediction of the combustion zone. A comprehensive study of different strut configurations and fuel injection locations has been conducted 20‐24 . It was observed that in order to reduce the pressure loss in the combustion and enhance efficiency, it was necessary to augment and accelerate the mixing between the air and the fuel.…”

Section: Introductionmentioning

confidence: 99%

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Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

et al. 2020

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Supersonic combustion ramjet (scramjet) is a variant of ramjet in which the combustion takes place at supersonic velocity. The flow physics inside the scramjet combustor is quite complex due to the fact that the mixing and completion of the combustion take place in a short time, which is of the order of milliseconds. This study focuses on flow characteristics within the combustion chamber of the scramjet engine that is designed to improve energy efficiency by enhancing combustion efficiency. The effect on combustion performance and thereby the energy efficiency on using strut-based flame stabilizer is evaluated at different positions. Reynolds averaged Navier-Stokes equations are solved with the Shear Stress Transport k-ω turbulence model. Single strut configuration is used to validate with the experimental data. Single strut is then compared with three-strut configuration. In the three-strut configuration, the location of the primary strut is kept constant, and the secondary struts are relocated in x and y directions. Combustion performance was evaluated for the cases of flow from primary strut only and through three struts. It was found that the placement of secondary strut in a three-strut configuration plays a vital role in improving energy efficiency. A maximum of 33.86% improvement in combustion efficiency was observed in comparison to the single strut combustor. A reduction in unburned fuel was observed, making the system more energy efficient. If the struts are not placed optimally, the combustion performance of the combustor was observed to be lower than that of a single-strut configuration. The shock reflection and expansion fans within the primary combustion zone and the secondary strut region enhance the combustion efficiency. The wall static pressure was observed to increase with the addition of secondary struts. For certain strut configurations, flow separation was seen on the combustor walls. If the secondary strut was placed close to the primary strut, combustion efficiency was found to enhance. It was seen that

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Section: Turbulence Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

et al. 2020

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“…Oevermann [33] considered numerical studies on a tw-dimensional (2D) scramjet combustor using the flamelet model and validated the flow parameters with the reported experimental outcomes of DLR [21,22]. Followed by Oevermann, many researchers simulated supersonic combustion typically by using the strut injector [24,34,35]. Xue et al [36] researched the shock wave emanating from the strut and illustrated that the oblique shock waves generated due to the strut inherently progress the scramjet engine air-fuel mixing and combustion efficiencies too.…”

Section: Introductionmentioning

confidence: 99%

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

et al. 2021

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This paper focuses on the influence of ramp locations upstream of a strut-based scramjet combustor under reacting flow conditions that are numerically investigated. In contrast, a computational study is adopted using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport (SST) k-ω turbulence model. The numerical results of the Deutsches Zentrum für Luft- und Raumfahrt or German Aerospace Centre (DLR) scramjet model are validated with the reported experimental values that show compliance within the range, indicating that the adopted simulation method can be extended for other investigations as well. The performance of the ramps in the strut-based scramjet combustor is analyzed based on parameters such as wall pressures, combustion efficiency and total pressure loss at various axial locations of the combustor. From the numerical shadowgraph, more shock interactions are observed upstream of the strut injection region for the ramp cases, which decelerates the flow downstream, and additional shock reflections with less intensity are also noticed when compared with the DLR scramjet model. The shock reflection due to the ramps enhances the hydrogen distribution in the spatial direction. The ignition delay is noticed for ramp combustors due to the deceleration of flow compared to the baseline strut only scramjet combustor. However, a higher flame temperature is observed with the ramp combustor. Because more shock interactions arise from the ramps, a marginal increase in the total pressure loss is observed for ramp combustors when compared to the baseline model.

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“…Various modification has been proposed by numerous scientist and research scholar in the direction of improved mixing [11][12][13] by means of fuel injection strategies, 14 geometrical parameters [15][16][17][18] boundary conditions [19][20][21] and a lot more. Among three types of fuel injection strategy, parallel fuel injection [22][23][24] is only taking more attention and widely use.…”

Section: Introductionmentioning

confidence: 99%

Impact of parametric variation on combustion characteristics of hydrogen‐fueled strut based scramjet combustor at supersonic speed

2020

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Supersonic combustion ramjet engine is more fascinating among all the airbreathing engines. Due to its higher thrust to weight ratio, researchers are more interested to get the superior combustion performance at the optimum boundary conditions. The flow field characteristics and combustion performance have been analysed with the help of Ansys 14.0 software. Generic scramjet combustor of German Aerospace Center (DLR) has been taken into consideration for comparison purpose and off design analysis has been conducted to investigate and analyse the changes. Two dimensional compressible Reynolds Averaged Navier-Stokes (RANS) turbulence model has been opted with the finite-rate/eddy-dissipation reaction model. K-ε two equation turbulence model has been selected to reach up to reasonable accuracy. Validation of the present work has been done with the help of both non-reacting and reacting type data from open literature. To choose the appropriate meshing of the computational model three different types of mesh elements, that is, coarse, medium and fine has been analysed and also grid independence analysis is performed. The present article objective is to get optimum boundary condition by changing the incoming air temperature and pressure at constant Mach number to connect the bridge between incoming air temperature and pressure to the change in velocity throughout the combustion chamber. The detailed understanding and explanation have been done by varying the temperature range of incoming air because of its major impact on combustion performance. Nonetheless, a small variation of air pressure will also discuss to observe the parameters which majorly influence while doing performance analysis. At the end the Optimum boundary condition for the present computation work is observed to be at 833 K temperature with 115 299 Pa pressure.

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Effect of parametric variation of strut layout and position on the performance of a typical two-strut based scramjet combustor

Cited by 114 publications

References 49 publications

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

Impact of parametric variation on combustion characteristics of hydrogen‐fueled strut based scramjet combustor at supersonic speed

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