Fundamental Scramjet Combustion Experiments Using Hydrocarbon Fuel

Vanyai, Tristan; Grieve, Sam; Street, Oliver; Denman, Zachary; McIntyre, Timothy J.; Veeraragavan, Ananthanarayanan; Wheatley, Vincent; Smart, Michael K.

doi:10.2514/1.b37472

Cited by 31 publications

(3 citation statements)

References 45 publications

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“…Vanyai et al investigated a scramjet combustor in a T4 free-piston shock tunnel at The University of Queensland. The shock tube provided supersonic airflow at a Mach number of 3.8, a temperature of 668-832 K, and a static pressure of 32.8-33.7 kPa [3]. Through this shock tube facility, it was possible to show that the pressure rise due to combustion is significant when the equivalence ratio is 0.3 or more.…”

Section: Introductionmentioning

confidence: 99%

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Lee

Han

et al. 2023

Aerospace

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Vitiation air heater (VAH) combustion characteristics for a direct-connect scramjet combustor (DCSC) were experimentally studied. The VAH consists of a head, modular chamber, and circular-to-rectangular shape transition (CRST) nozzle. The CRST nozzle transforms the circular cross-sectioned rocket-type VAH into a rectangular cross-sectioned scramjet combustor. The CRST nozzle exit Mach numbers at the top, middle, and bottom were measured using a tungsten wedge. The oblique shock formed by the wedge was captured using Schlieren visualization and recorded with a high-speed camera. The θ-β-M relation showed that the exit Mach number was 2.04 ± 0.04 with a chamber pressure of 1.685 ± 0.07 MPa. With the VAH design point verified, preliminary scramjet combustor ignition tests were conducted. As the fuel was not auto-ignited by the vitiated air, the forced ignition method, in which VAH ignition flame ignites the scramjet fuel, was used. The Schlieren images showed that a cavity shear layer combustion mode was formed and also showed that the forced ignition method could be used as a reference model for the ignitor-ignition method.

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Section: Introductionmentioning

confidence: 99%

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Lee

Han

et al. 2023

Aerospace

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“…However, the mixing, ignition, and stable combustion of fuel and air within the limited distance of the chamber at such high speeds remain critical issues. To address this, numerous experimental and numerical simulation studies of ramjet combustors with various flame stabilization devices have been conducted worldwide in the past several decades [1][2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Investigation of Very Large Eddy Simulation Method for Applications of Supersonic Turbulent Combustion

Yan

Cao

et al. 2023

Aerospace

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The very large eddy simulation (VLES) method was investigated for supersonic reacting flows in the present work. The advantages and characteristics of the VLES model and the widely used improved delayed detached eddy simulation (IDDES) method were revealed through a supersonic ramped-cavity cold flow. Compared to the IDDES model, the VLES model transformed from RANS mode to LES mode faster, resulting in a smaller gray region caused by the mode transition. However, the original volume-averaging truncation length scale could lead to poor predictions of the velocity profiles and wall pressure distribution. By introducing a hybrid truncation length scale combining the maximum grid length and the shear layer adaptive (SLA) length with different coefficients, the accuracy of the VLES method was significantly improved, and the issue of the low shear layer position was solved. Moreover, owing to the resolution control function, the VLES method could adaptively model more turbulent kinetic energy and maintain a good accuracy in a coarser mesh. Finally, the modified VLES method was applied in conjunction with a hybrid combustion model constructed by the partially stirred reactor (PaSR) model and the Ingenito supersonic combustion model (ISCM) in simulations of the supersonic flame in the DLR scramjet combustor. After introducing the correction of the molecular collision frequency by the ISCM, the results obtained by the hybrid combustion model were more consistent with the experimental results, especially for the time-averaging temperature profile in the ignition zone.

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“…Although there are many difficult problems with the study of the cavity-assisted axisymmetric scramjet, there are still several studies in recent years. Vanyai et al [13] carried out an experiment on the axisymmetric combustor assisted with the cavity at flight condition of Mach 7-8 and found that the flame structure became pretty different with the variation of the equivalence ratio. An axisymmetric scramjet with a cavity was experimentally and numerically studied by Denman et al [14].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of an Axisymmetric Model Scramjet Assisted with Cavity of Different Aft Wall Angles

Sun

Zhao

et al. 2021

International Journal of Aerospace Engineering

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An axisymmetric model scramjet assisted with cavity flameholder is numerically investigated. Three-dimensional Reynolds-averaged Navier-Stokes simulation is carried out to reveal the fuel mixing and combustion characteristics. The simulation results show reasonable agreements with experimental data. The analysis indicates that the axisymmetric and rectangular scramjet has some similarities to the cavity shear layer in the nonreacting flow field. The configuration of the cavity shear layer changes hugely due to the significant chemical reaction and heat release in the reacting flow field. Typically, two more configurations with different cavity aft wall angles are compared with the experimental configuration to optimize the configuration of the cavity. When the cavity aft wall angle is small, the cavity shear layer bends to the cavity floor and more fuel enters into and stays in the cavity, which results in poor fuel mixing performance. With the increase of the aft wall angle, the fuel distributes more uniformly and the fuel mixing efficiency improves. In the reacting flow field, the volume of the cavity full of hot products and free radicals increases while the interaction between the cavity and main flow decreases with the increase of the aft wall angle. The improved combustion efficiency shows that larger cavity volume weighs more than reduced interaction between the cavity and main flow. The combustion is more violent in the case with a larger aft wall angle. Therefore, a proper increase of the aft wall angle is beneficial to the performance of cavity-assisted axisymmetric scramjet when designing the cavity flameholder.

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Fundamental Scramjet Combustion Experiments Using Hydrocarbon Fuel

Cited by 31 publications

References 45 publications

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Investigation of Very Large Eddy Simulation Method for Applications of Supersonic Turbulent Combustion

Numerical Investigation of an Axisymmetric Model Scramjet Assisted with Cavity of Different Aft Wall Angles

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