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Blast Wave-Induced Mixing in a Laser Ignited Hypersonic Flow

[+] Author and Article Information
Nicholas Gibbons

Center for Hypersonics,
School of Mechanical and Mining Engineering,
The University of Queensland,
St. Lucia, Brisbane 4072
e-mail: n.gibbons@uq.edu.au

Rolf Gehre, Stefan Brieschenk, Vincent Wheatley

Center for Hypersonics,
School of Mechanical and Mining Engineering,
The University of Queensland,
St. Lucia, Brisbane 4072

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received December 1, 2016; final manuscript received October 30, 2017; published online December 20, 2017. Assoc. Editor: Ben Thornber.

J. Fluids Eng 140(5), 050902 (Dec 20, 2017) (10 pages) Paper No: FE-16-1785; doi: 10.1115/1.4038397 History: Received December 01, 2016; Revised October 30, 2017

A laser ignition system suitable for a hypersonic scramjet engine is considered. Wall-modeled large eddy simulation (LES) is used to study a scramjet-like geometry with a single hydrogen injector on the inlet, at a Mach 8 flight condition with a total enthalpy of 2.5 MJ. Detailed chemical kinetics and high fidelity turbulence modeling are used. The laser forms a kernel of high temperature plasma inside the fuel plume that briefly ignites the flow and leads to massive disruption of the flow structures around the jet, due to the expanding plasma kernel driving a blast wave that collides with the surrounding flow. The blast wave produces vorticity as it passes through the fuel–air interface, but comparably less than that produced by the jetting of the hot gas affected by the laser as it expands outward into the crossflow. The remnant of the plasma rolls up into a powerful vortex ring and noticeably increases the fuel plume area and the volume of well mixed reactants present in the simulation. These results indicate that the laser ignition system does more than just supply the energy to ignite the flow; it also substantially alters the flow structure and the mixing process.

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Figures

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Fig. 2

Flow domain colored by different wall boundaries and coarsened symmetry plane grid

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Fig. 3

Flow domain shape in x–y plane with dimensions in mm. Z dimension is planar to a depth of 70 mm, except for the injector.

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Fig. 4

Signal propagation time in the fine grid, close-up of injector symmetry plane

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Fig. 8

Instantaneous hydrogen mass fraction color map, showing jet symmetry plane. Top: Medium grid. Bottom: Fine grid.

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Fig. 9

Integrated yplus averaged over the z direction and plotted against downstream distance

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Fig. 5

Time-averaged hydrogen mass fraction (medium grid) with streamwise velocity plot overlay

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Fig. 6

Time-averaged mixedness M¯ (see Eq. (13)), integrated over planes normal to the streamwise direction

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Fig. 1

Experimental setup used by Ref. [4]

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Fig. 7

Time-averaged fraction of resolved TKE. Top: Medium grid. Bottom: Fine grid.

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Fig. 10

Vortex visualization using the TDM and λ2 = –5 × 1011 criterion and center plane H2 mass fraction. Top: t = 0.0 μs. Bottom: t = 16.0 μs.

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Fig. 11

Z-components of the vorticity vector, compressibility term, and baroclinic production

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Fig. 12

Visualization of the reacting fraction in fuel-rich and fuel-lean cases

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Fig. 13

Vertically integrated mixedness over time and mixedness color map

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Fig. 14

Vertically integrated mixedness, before and after LIP ignition

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