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  • 1
    Online Resource
    Online Resource
    The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor
    MDPI AG ; 2021
    In:  Energies Vol. 14, No. 4 ( 2021-02-05), p. 831-
    Details
    In: Energies, MDPI AG, Vol. 14, No. 4 ( 2021-02-05), p. 831-
    Abstract: 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.
    Type of Medium: Online Resource
    ISSN: 1996-1073
    URL: Article
    DOI: 10.3390/en14040831
    Language: English
    Publisher: MDPI AG
    Publication Date: 2021
    detail.hit.zdb_id: 2437446-5
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  • 2
    Online Resource
    Online Resource
    Numerical investigations on the influence of double ramps in a strut based scramjet combustor
    SAGE Publications ; 2023
    In:  International Journal of Engine Research Vol. 24, No. 5 ( 2023-05), p. 2025-2038
    Details
    In: International Journal of Engine Research, SAGE Publications, Vol. 24, No. 5 ( 2023-05), p. 2025-2038
    Abstract: This numerical study addresses the performance of double ramps in a strut injection scramjet combustor. Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport SST k-[Formula: see text] turbulence model are used for numerical analysis. The dual ramps are located symmetrically at the top and bottom wall of a scramjet combustor downstream of the strut injector. The influence of the location of ramps in the scramjet combustor is analyzed based on the key parameters such as shock waves, static pressures, and temperature distribution across the combustor, which are verified with available DLR scramjet experimental data that show similar acceptable values within the range. Simulation is extended for the investigation of other configurations. The performance of the scramjet configurations has been analyzed using the variables such as shock patterns, Mach number contours, wall static pressures, mass fractions of the reactants and products, combustion efficiency, and stagnation pressure loss of combustor. Numerical shadowgraph indicates that numerous shock reflections occur for the dual ramp cases that decelerate the combustor’s flow downstream. In addition, the recirculation regions are created for the dual ramp cases, which help in anchoring the flame. The static pressure distributions show the variation of peaks due to shock patterns and their interactions. The combustion efficiency increases as the ramps are positioned downstream of the strut injector. The mass fractions of reactants and products indicate complete combustion of the hydrogen issued from the combustor in the vicinity of the cavities. The total pressure loss for the DLR strut model is comparatively lower than dual ramp cases due to the multiple shocks from the ramp decelerating the flow downstream of the combustor.
    Type of Medium: Online Resource
    ISSN: 1468-0874 , 2041-3149
    URL: Article
    DOI: 10.1177/14680874221107137
    RVK:
    ZG 1100
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2023
    detail.hit.zdb_id: 2030603-9
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  • 3
    Online Resource
    Online Resource
    The implications of dual cavity location in a strut-mounted scramjet combustor
    Elsevier BV ; 2023
    In:  International Communications in Heat and Mass Transfer Vol. 145 ( 2023-06), p. 106855-
    Details
    In: International Communications in Heat and Mass Transfer, Elsevier BV, Vol. 145 ( 2023-06), p. 106855-
    Type of Medium: Online Resource
    ISSN: 0735-1933
    URL: Article
    DOI: 10.1016/j.icheatmasstransfer.2023.106855
    Language: English
    Publisher: Elsevier BV
    Publication Date: 2023
    detail.hit.zdb_id: 2020560-0
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  • 4
    Online Resource
    Online Resource
    Influence of wall mounted ramps on DLR strut scramjet combustor under non-reacting flow field
    Elsevier BV ; 2022
    In:  Materials Today: Proceedings Vol. 56 ( 2022), p. 3002-3008
    Details
    In: Materials Today: Proceedings, Elsevier BV, Vol. 56 ( 2022), p. 3002-3008
    Type of Medium: Online Resource
    ISSN: 2214-7853
    URL: Article
    DOI: 10.1016/j.matpr.2021.11.347
    Language: English
    Publisher: Elsevier BV
    Publication Date: 2022
    detail.hit.zdb_id: 2797693-2
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  • 5
    Online Resource
    Online Resource
    Reviewing the Challenges in Maintaining the Reliability and Accuracy of IOT Systems for Remaining Useful Life Prediction
    IOP Publishing ; 2021
    In:  IOP Conference Series: Materials Science and Engineering Vol. 1128, No. 1 ( 2021-04-01), p. 012010-
    Details
    In: IOP Conference Series: Materials Science and Engineering, IOP Publishing, Vol. 1128, No. 1 ( 2021-04-01), p. 012010-
    Abstract: Internet of things (IoT) has been implemented in aviation predictive maintenance in recent years for the enhancement of better maintenance prediction, to reduce downtime, unnecessary maintenance actions, increase safety, increase system readiness, and refine the management process and to improve component design. The IoT system in predictive maintenance is very optimistic in gathering and analysing, predicting the component failures and to determine the remaining useful life of a systems. Since Remaining useful life of an system is defines as the length from the current time to the end of its useful life. Due to its futuristic increasing demand of IoT in aviation maintenance, the biggest challenge is to ensuring the reliability and accuracy of any specific IoT system allotted for monitoring aircraft components in the near future. Hence, this review paper clearly explains the challenges associated with IoT systems on predicting Remaining useful life.
    Type of Medium: Online Resource
    ISSN: 1757-8981 , 1757-899X
    URL: Article
    DOI: 10.1088/1757-899X/1128/1/012010
    Language: Unknown
    Publisher: IOP Publishing
    Publication Date: 2021
    detail.hit.zdb_id: 2506501-4
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  • 6
    Online Resource
    Online Resource
    The Effect of Ramp Location in a Strut Based Scramjet Combustor under non reacting flow field
    IOP Publishing ; 2021
    In:  IOP Conference Series: Materials Science and Engineering Vol. 1128, No. 1 ( 2021-04-01), p. 012006-
    Details
    In: IOP Conference Series: Materials Science and Engineering, IOP Publishing, Vol. 1128, No. 1 ( 2021-04-01), p. 012006-
    Abstract: The scramjet engine is considered to be the high-speed propulsive system for hypersonic air-breathing vehicles. Researchers focus on various geometries of strut injectors to enhance the mixing and combustion efficiencies of the scramjet combustor. This paper reveals the non-reacting flow characteristics of various ramp locations in a scramjet combustor with strut injection. The ramps are symmetrically placed at three different locations upstream of the strut within the combustor. Air enters into the combustor inlet with Mach number 2, and the fuel is injected at the sonic velocity from the strut. The 2D supersonic flow characteristics are numerically investigated using ANSYS 18.0 software. The steady-state flow simulations are performed in this study. The flow field is modelled using RANS equations, and the k-ω SST turbulence model and default constants are chosen to investigate the flow characteristics within the combustor. The flow characteristics of the ramp based DLR scramjet combustors are compared with the baseline DLR scramjet model. The computational results are validated with the experimental data. The shock wave interaction from the ramps enhances the distribution of hydrogen in the lateral direction of the flow than the baseline strut configuration. The ramps create recirculation regions that could enhance fuel-air mixing. The ramp induced strut based DLR scramjet engine provides increased total pressure loss of the baseline DLR scramjet.
    Type of Medium: Online Resource
    ISSN: 1757-8981 , 1757-899X
    URL: Article
    DOI: 10.1088/1757-899X/1128/1/012006
    Language: Unknown
    Publisher: IOP Publishing
    Publication Date: 2021
    detail.hit.zdb_id: 2506501-4
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