Finite Rate Chemistry Large-Eddy Simulation of Self-Ignition in Supersonic Combustion Ramjet

Berglund, Magnus; Fedina, E.; Fureby, Christer; Tegnér, Jon K.; Sabelnikov, Vladimir

doi:10.2514/1.43746

Cited by 156 publications

(75 citation statements)

References 16 publications

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“…To solve this problem, some fuel injection techniques have been proposed. The strut [5][6][7][8][9][10][11][12][13][14], the cavity [15][16][17][18], the cantilevered ramp [4], the backward facing step [19][20][21] and the combination [22][23][24][25], whose principle is to generate vorticity in the vicinity of the walls of the combustor. The region forming the vorticity, namely the recirculation zone, has low flow velocity.…”

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confidence: 99%

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Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

et al. 2011

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The flame-holding mechanism in hypersonic propulsion technology is the most important factor in prolonging the duration time of hypersonic vehicles. The two-dimensional coupled implicit Reynolds-averaged Navier-Stokes equations, the shear-stress transport k- turbulence model and the finite-rate/eddy-dissipation reaction models were used to simulate the combustion flow field of a typical strut-based scramjet combustor. We investigated the effects of the hydrogen-air reaction mechanism and fuel injection temperature and pressure on the parametric distributions in the combustor. The numerical results show qualitative agreement with the experimental data. The hydrogen-air reaction mechanism makes only a slight difference in parametric distributions along the walls of the combustor, and the expansion waves and shock waves exist in the combustor simultaneously. Furthermore, the expansion wave is formed ahead of the shock wave. A transition occurs from the shock wave to the normal shock wave when the injection pressure or temperature increases, and the reaction zone becomes broader. When the injection pressure and temperature both increase, the waves are pushed out of the combustor with subsonic flows. When the waves are generated ahead of the strut, the separation zone is formed in double near the walls of the combustor because of the interaction of the shock wave and the boundary layer. The separation zone becomes smaller and disappears with the disappearance of the shock wave. Because of the horizontal fuel injection, the vorticity is generated near the base face of the strut, and this region is the main origin for turbulent combustion. , hypersonic propulsion technology has drawn increasing attention from researchers. However, the flame-holding mechanism in the scramjet combustor cannot satisfy the requirement for cruising a long time in near-space [3] because of the short residence time of the mixture remaining in the supersonic flow, which is in the order of milliseconds [4]. This restricts improvement of the aerodynamic performance of hypersonic vehicles. To solve this problem, some fuel injection techniques have been proposed. The strut [5][6][7][8][9][10][11][12][13][14], the cavity [15][16][17][18], the cantilevered ramp [4], the backward facing step [19][20][21] and the combination [22][23][24][25], whose principle is to generate vorticity in the vicinity of the walls of the combustor. The region forming the vorticity, namely the recirculation zone, has low flow velocity. In this region the fuel mixes with the supersonic flow and the mixture can stay in the scramjet combustor for a long time. Zou et al. [6] have used a newly-proposed partiallyresolved numerical simulation procedure to investigate turbulent combustion in a two-dimensional DLR scramjet engine, and the large-scale turbulence was defined by the temporal filtering. Oevermann [7] has used a two-equation k- turbulence model combined with a stretched laminar

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“…Furthermore, a largeeddy simulation has been used to simulate the flow field downstream of a three-dimensional strut-based injection system in a scramjet combustor [9,10]. Three different hydrogen-air reaction mechanisms have been introduced to perform the turbulent combustion simulation, namely the one-, two-and seven-step mechanisms [11].…”

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Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

et al. 2011

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“…A few of these include the injection of gaseous fuel jets in a natural gas engine [1,2] or a supersonic combustor [3,4], discharge of chimney gases into the atmosphere [5,6], and thrust control of rockets and V/STOL aircraft via jets [7,8]. In most of these applications, an overall control of the fluid mechanics of the flow is required to improve the quality of the end process.…”

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Flow characteristic of highly underexpanded jets from various nozzle geometries

Zhou

Yao

et al. 2017

Applied Thermal Engineering

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“…A constant turbulent Schmidt number Sc t = 0.80 and laminar/turbulent Pr ratio of 0.8 were assumed. Combustion was modeled by the modi¦ed 9 species (N 2 , O 2 , H 2 , H 2 O, OH, O, H, HO 2 , and H 2 O 2 ), 19-step chemical kinetics model of Jachimowski [11], where nitrogen reactions and turbulence chemistry interactions were ignored [12,13].…”

Section: Numerical Setupmentioning

confidence: 99%

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

Rabadan

2013

Progress in Propulsion Physics

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Numerical investigations of a hydrogen-fueled scramjet combustor at cruise §ight conditions of Mach 8 at an altitude of 30 km have been performed. Two combustor con¦gurations were investigated: a single-stage combustor with a central strut injector and a two-staged combustor combining the central strut and wall-mounted ramp injectors. These numerical simulations are aimed to study the §ow structure, supersonic mixing, autoignition, and combustion for the present combustor con¦gurations. A turbulent §ow from a separate intake calculation was used as in §ow condition for the combustor. A better performance for the two-staged combustor con¦guration was observed. The combination of the central strut injection together with the wall-ramp injection improved the turbulent mixing and, consequently, the combustion process. Inside the supersonic combustion chamber, the autoignition zone occurred downstream of the injectors, and combustion takes place accompanied by high heat release and pressure rise. As the equivalence ratio was increased, the combustion became stronger causing an upstream displacement of the shock train producing di¨erent pressure variations. For the two-staged combustor con¦guration, the location of the autoignition zone was found to appear further upstream compared to single-stage combustor. Mixing was improved by addition of the second-stage injection. The in §uence of the wall temperature was also investigated showing an e¨ect on the combustion pressure rise and the length and location of the shock train.

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Finite Rate Chemistry Large-Eddy Simulation of Self-Ignition in Supersonic Combustion Ramjet

Cited by 156 publications

References 16 publications

Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

Flow characteristic of highly underexpanded jets from various nozzle geometries

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

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