Scalability of Ethylene Gaseous Jets for Fueling High-Speed Air-Breathing Combustors

Lin, Kuo-Cheng; Carter, Campbell; Gruber, Mark; Raffoul, Charbel

doi:10.2514/6.2009-1423

Cited by 20 publications

(31 citation statements)

References 12 publications

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“…Considered were two turbulent mass diffusivity models due to Xiao, et al [6] and Brinckman, et al [3], as well as a new scalar flux model based on that of Younis, Speziale, and Clark [9]. The LES/RANS closure was validated by comparison with data from the experiment of Lin, et al [12], including Raman scattering data of injected ethylene mole fraction at different planes of the flow and NO-PLIF snapshots of the injected gas plume. The simulation achieved generally good agreement with the experiment, although jet penetration and entrainment was slightly under-predicted.…”

Section: Resultsmentioning

confidence: 99%

“…The basic first-order upwind method is extended to higher-order using a low-dissipation variant (LD-PPM) formed by blending the piecewise-parabolic method (PPM, [17]) with a fourth-order central scheme according to a flow-dependent switch developed by Ducros and co-workers [18]. The experiment simulated in this study was based on the sonic injection work of Lin, et al [12], the layout of which is shown in Figure 1. A Mach 2.0 air stream moves through a rectangular test section, 131mm high by 152mm wide.…”

Section: Methodsmentioning

confidence: 99%

“…Largescale turbulence is plainly visible in the spreading injectant plume. Validation of the LES/RANS data was accomplished by comparing the ethylene mole fraction at different Y-Z planes with Raman scattering and NO-PLIF data obtained by Lin, et al [12]. Figure 4, compiled by Boles, et al [19] shows a snapshot of the ethylene mass fraction taken at the X-Y centerline for both the simulation and the experiment.…”

Section: Calculation Detailsmentioning

confidence: 99%

“…A sonic ethylene injection experiment by Lin, et al [12] was simulated using LES/RANS modeling. After validating the results with experimental data, the injected gas was replaced with argon and helium and the simulation repeated.…”

Section: Introductionmentioning

confidence: 99%

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LES/RANS Simulations of Turbulent Mixing in Gas Plumes

Zilberter¹,

Edwards²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A hybrid Large Eddy Simulation/Reynolds-averaged Navier-Stokes (LES/RANS) model is used to simulate a set of high-speed experiments of sonic gas injection into a Mach 2.0 air stream (Lin, et al, AIAA Paper 2009-1423) in order to gather data for the assessment of two RANS-level models for the turbulent mass diffusivity (Xiao, et al., AIAA Journal, Vol. 44, Brinckman, et al., AIAA Journal, Vol. 46). The LES/RANS closure is validated by comparing the injected ethylene mole fraction with Raman scattering and NO-PLIF data from the experiment. The simulation is in general good agreement with the experiment but slightly under-predicts the level of jet entrainment. Two further simulations are conducted with the ethylene injectant replaced with helium and argon. The LES/RANS data is mined to extract resolved turbulence statistics which are then used to assess the performance of both mass diffusivity models. It is found that both models perform poorly in the context of a classical gradient-diffusion formulation for the scalar flux; a new formulation is proposed which improves the performance of both models. The LES/RANS data is then used to optimize the model constants of both models. Further evaluation of the optimized models shows that they are in good agreement with LES/RANS values of scalar turbulence production for both the sonic injection flow and a planar mixing layer (Barre, et al., Journal of Fluid Mechanics, Vol. 259).

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Section: Resultsmentioning

confidence: 99%

Section: Methodsmentioning

confidence: 99%

Section: Calculation Detailsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

LES/RANS Simulations of Turbulent Mixing in Gas Plumes

Zilberter¹,

Edwards²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…The second fuel mixing problem considered attempts to reproduced one of the sets of experimental measurements obtained by Lin et al 21,22 Data is for a flush 30° sonic (M j = 1.0) ethylene (C 2 /H 4 ) jet issuing into a M ∞ =2.0 (U ∞ = 518m/s, T ∞ = 166K) crossflow. Here, the case with a jet-to-crossflow momentum ratio of J = 1.0 is considered.…”

Section: Ethylene Injectionmentioning

confidence: 99%

DDES of Aeropropulsive Flows Based on an Extended k-? RANS Model

Rodebaugh

Brinckman

Dash

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Aeropropulsive flows may contain localized separated flow regions whose analysis using RANS methodology may be inadequate, particularly so for massively separated flows having unsteady/oscillatory features. DES-type methods provide for the improved analysis of these local regions, and can often demarcate the zones to be analyzed using RANS or LES methodology in an automated fashion. The DDES implementation described utilizes an extended k-ε model in RANS regions containing a number of unique features catered to analyzing aeropropulsive flows. Several aeropropulsive cases of interest are considered for which test data is available. Cases include: a supersonic base flow calculation; a transverse supersonic air jet interacting with a subsonic airtstream; and two angled fuel simulant jets (M j = 2.5 helium jet and M j = 1.0 ethylene jet) injected into a M ∞ = 2.0 airstream. The results obtained for the supersonic base flow case as well for the transverse air jet in a crossflow case, both compare favorably with the experimental measurements. The predictions for the helium injection case also agree reasonably well with the experimental data. The ethylene case case was not as well predicted which may be due to the RANS representation of the approach boundary layer for this low momentum ratio case (as also pointed out by other investigators).

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