Experimental Study of Strut Injectors in a Supersonic Combustor Using OH-PLIF

Sunami, Tetsuji; Magre, P.; Bresson, Alexandre; Grisch, Frédéric; Orain, Mikaël; Kodera, Masatoshi

doi:10.2514/6.2005-3304

Cited by 51 publications

(26 citation statements)

References 15 publications

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“…Good agreement with the limited reference data available for these two cases is observed. In order to further validate the LES models, comparisons are also made with experimental (Sunami et al 2005); circles, experimental hot (Sunami et al 2005); black solid lines, LES cold; grey solid lines, LES hot seven-step EDC; grey dashed lines, LES hot seven-step TFM). data in various laboratory combustors, such as an open low-swirl burner, resulting in a stratified mixture, and a modern gas turbine premixer connected to a round can combustor.…”

Section: Discussionmentioning

confidence: 99%

“…LES has proven successful in this (Génin et al 2003;Berglund & Fureby 2006), and recently the influence of the chemical kinetics on the self-ignition in vitiated hot supersonic air was also studied using one-, twoand seven-step mechanisms (Davidenko et al 2006). The ONERA/JAXA supersonic combustion rig (Sunami et al 2005) was used by Berglund et al (2008) and in the present study, and consists of an air-vitiation heater (providing an N 2 /H 2 O mixture with a mass-fraction distribution of 0.23 : 0.70 : 0.07 at a temperature of 830 K, a velocity of 1449 m s K1 and a pressure of 34.2 kPa) and a constant-area duct connected to the diverging area combustor. The flame is stabilized by a wedge-shaped flameholder of height h, from which H 2 is injected at the top and bottom walls and at the base into the vitiated hot supersonic airstream, figure 3a.…”

Section: High-speed Ramjet and Scramjet Combustionmentioning

confidence: 99%

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Large eddy simulation modelling of combustion for propulsion applications

Fureby

2009

Phil. Trans. R. Soc. A.

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Predictive modelling of turbulent combustion is important for the development of airbreathing engines, internal combustion engines, furnaces and for power generation. Significant advances in modelling non-reactive turbulent flows are now possible with the development of large eddy simulation (LES), in which the large energetic scales of the flow are resolved on the grid while modelling the effects of the small scales. Here, we discuss the use of combustion LES in predictive modelling of propulsion applications such as gas turbine, ramjet and scramjet engines. The LES models used are described in some detail and are validated against laboratory data-of which results from two cases are presented. These validated LES models are then applied to an annular multi-burner gas turbine combustor and a simplified scramjet combustor, for which some additional experimental data are available. For these cases, good agreement with the available reference data is obtained, and the LES predictions are used to elucidate the flow physics in such devices to further enhance our knowledge of these propulsion systems. Particular attention is focused on the influence of the combustion chemistry, turbulence-chemistry interaction, selfignition, flame holding burner-to-burner interactions and combustion oscillations.

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Section: Discussionmentioning

confidence: 99%

Section: High-speed Ramjet and Scramjet Combustionmentioning

confidence: 99%

Large eddy simulation modelling of combustion for propulsion applications

Fureby

2009

Phil. Trans. R. Soc. A.

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“…For the application of the struts, technical difficulties are an increase in the distance (combustor length) to achieve adequate mixing [7] and flame stabilization, especially for a thin strut. Previous experiments [8] and numerical simulations [9] demonstrate flame-holding of the strut-based scramjet configure depends on the subsonic recirculation created in its base, and therefore an increase of the thickness of the strut (i.e., of the blockage ratio in the combustor channel) enhances the capability of the strut injector for ignition and stabilization of the flame. However, a thick strut can lead to significant drag and total pressure losses increase.…”

Section: Introductionmentioning

confidence: 99%

Richtmyer-Meshkov Instability Induced Mixing Enhancement in the Scramjet Combustor with a Central Strut

Yang

Chang

Bao

2014

Advances in Mechanical Engineering

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Experimental and numerical study of Richtmyer-Meshkov instability (RMI) induced mixing enhancement has been conducted in a liquid-fueled scramjet engine with a central strut. To generate the RMI in the scramjet engine, transverse high temperature jets are employed downstream the strut injector. Compared to the transverse ordinary temperature jet, the jet penetration into the supersonic airstream of high temperature jet increases by 60%. The numerical results indicate that the RMI phenomenon markedly enhances the mixing efficiency (up to 43%), which is necessary to initiate the chemical reactions. Ground experiments were carried out in the combustor, which verify the numerical method from the perspective of wall pressures of the combustor. In particular, the experiment results indicate that the RMI can benefit flame-holding due to the mixing enhancement.

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“…The development of largescale structures of mixing layer relates to the instability of recirculation zone and recompression shock that behind the recirculation zone. The former studies [6,7] indicate that flame-holding depends on the recirculation zone behind the strut. Increasing the thickness of the strut can enhance the mixing and stability of the flame.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of Large-Scale Structures in Supersonic Planar Mixing Layer with Finite Thickness

Zhang

Chen

et al. 2014

Advances in Mechanical Engineering

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Nanoparticle-based planar laser scattering (NPLS) experiments and large eddy simulation (LES) were launched to get the fine structure of the supersonic planar mixing layer with finite thickness in the present study. Different from the turbulent development of supersonic planar mixing layer with thin thickness, the development of supersonic planar mixing layer with finite thickness is rapidly. The large-scale structures of mixing layer that possess the characters of quick movement and slow changes transmit to downriver at invariable speed. The transverse results show that the mixing layer is strip of right and dim and possess 3D characteristics. Meanwhile the vortices roll up from two sides to the center. Results indicate that the higher the pressure of the high speed side is, the thicker the mixing layer is. The development of mixing layer is restrained when the pressure of lower speed side is higher. The momentum thickness goes higher with the increase of the clapboard thickness. Through increasing the temperature to change the compression can affect the development of the vortices. The present study can make a contribution to the mixing enhancement and provide initial data for the later investigations.

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Experimental Study of Strut Injectors in a Supersonic Combustor Using OH-PLIF

Cited by 51 publications

References 15 publications

Large eddy simulation modelling of combustion for propulsion applications

Large eddy simulation modelling of combustion for propulsion applications

Richtmyer-Meshkov Instability Induced Mixing Enhancement in the Scramjet Combustor with a Central Strut

Characteristics of Large-Scale Structures in Supersonic Planar Mixing Layer with Finite Thickness

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