Prediction of Combustion Instability with Detailed Chemical Kinetics

Sardeshmukh, Swanand V.; E, William E Anderson lMatthew; Sankaran, Venkateswaran

doi:10.2514/6.2015-1826

Cited by 36 publications

(13 citation statements)

References 17 publications

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“…Similar tests are then performed on high-fidelity (full-order) 2D snapshots of pressure from a simulation of the CVRC. 39 The simulation was performed on a 110,826-node mesh with the GRI 1.2 hydrocarbon reaction mechanism set consisting of 32 chemical species and 177 reactions. Snapshots of the full-order data were recorded every 5µs and 1025 snapshots are taken in total.…”

Section: B Axisymmetric (2d) Resultsmentioning

confidence: 99%

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Reduced-Order Modeling of Model Rocket Combustors

Duraisamy

2017

53rd AIAA/SAE/ASEE Joint Propulsion Conference

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This work reports preliminary results on the application of projection-based reducedorder models (ROMs) to the study of combustion dynamics in liquid-fueled rocket engines. Specifically, quasi-one-dimensional and axisymmetric (two-dimensional) models of a single element rocket combustor are explored. In the one-dimensional case, a POD-Galerkinbased ROM is shown to accurately reproduce the evolution of pressure perturbations over a wide region in parameter space. Next, the viability of sampling/interpolation techniques in accelerating ROM solutions is explored. Three techniques-the discrete empirical interpolation method (DEIM), a QR decomposition-based DEIM (QDEIM) and an adaptive technique (ADEIM) are used to reconstruct the solution in the entire domain based on sparse samples. All three techniques are shown to yield a low reconstruction error based on a very small fraction of sampling points (< 1% for the axisymmetric case). The ADEIM, by virtue of dynamically adapting the basis functions and sampling points, is seen to reduce the reconstruction error considerably in comparison to the DEIM/QDEIM, suggesting its viability in predictive ROMs of realistic rocket combustors.

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Section: B Axisymmetric (2d) Resultsmentioning

confidence: 99%

“…Predictive sampling/reconstruction tests were performed on data from the quasi-1D solver as well as axisymmetric (2D) simulations. 39 In the 1D test, the pressure was reconstructed in the entire domain using 12.5% of the points. The static methods achieved a reconstruction error below 3% and ADEIM further reduced the error to below 0.5%.…”

Section: Discussionmentioning

confidence: 99%

Reduced-Order Modeling of Model Rocket Combustors

Duraisamy

2017

53rd AIAA/SAE/ASEE Joint Propulsion Conference

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“…Table 4 summarizes the frequencies observed at limit cycle using pressure and velocity time-lag RF. The values are compared with experimental and multidimensional data reported by Sardeshmukh et al 27 and Harvazinski et al 10 Computing the PSD of pressure signals at limit cycle, it is possible to clearly identify the resonance frequencies whose values are in good agreement with those obtained by numerical simulations from which RF parameters have been extracted. 27 This proves that quasi-1D model is able to reproduce the multidimensional behavior in terms of frequency response.…”

Section: Nonlinear Regimementioning

confidence: 85%

“…The parameters to be included in the characterization of RFs have been taken according to Frezzotti et al 25,26 and are listed in Table 3. These parameters have been inferred by the results of the two-dimensional simulations performed by Sardeshmukh et al 27 In particular, the sampling location for pressure and velocity, longitudinal mode for pressure and velocity, respectively. The time lag has been estimated evaluating the crosscorrelation between the signal of pressure or velocity, in the case of pressure time lag and velocity time lag, respectively, and the heat release rate integrated in the chamber.…”

Section: Nonlinear Regimementioning

confidence: 99%

Numerical issues in modeling combustion instability by quasi-1D Euler equations

Frezzotti

D'Alessandro

Favini

et al. 2017

International Journal of Spray and Combustion Dynamics

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The present work is devoted to investigation of numerical issues related to combustion instability simulation through a quasi-1D Eulerian solver. The main aspects addressed are the choice of a suitable multispecies model and heat release response function formulation. Experimental data and high fidelity simulation results, available in literature, are reproduced with acceptable approximation. Main features of the flow field at limit cycle are shown. Moreover, a parametric study has been performed on time-lag response function characteristic parameters, leading to important conclusions on the pertinence of each assumption in the frame of a nonlinear tool

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“…These simulations used either one-or two-step global chemical mechanisms. Sardeshmukh et al [30] significantly improved oscillation amplitude predictions for their axisymmetric calculations by using the LCM combustion model with the GRI-Mech 1.2 detailed mechanism. However, 32 species transport equations were solved, making the computational cost prohibitively expensive.…”

Section: Introductionmentioning

confidence: 99%

The impacts of three flamelet burning regimes in nonlinear combustion dynamics

Nguyen

Sirignano

2018

Combustion and Flame

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Axisymmetric simulations of a liquid rocket engine are performed using a delayed detached-eddy-simulation (DDES) turbulence model with the Compressible Flamelet Progress Variable (CFPV) combustion model. Three different pressure instability domains are simulated: completely unstable, semi-stable, and fully stable. The different instability domains are found by varying the combustion chamber and oxidizer post length. Laminar flamelet solutions with a detailed chemical mechanism are examined. The β Probability Density Function (PDF) for the mixture fraction and Dirac δ PDF for both the pressure and the progress variable are used. A coupling mechanism between the volumetric Heat Release Rate (HRR) and the pressure in an unstable cycle is demonstrated. Local extinction and reignition is investigated for all the instability domains using the full S-curve approach. A monotonic decrease in the amount of local extinctions and reignitions occurs when pressure oscillation amplitude becomes smaller. The flame index is used to distinguish between the premixed and nonpremixed burning mode in different stability domains. An additional simulation of the unstable pressure oscillation case using only the stable flamelet burning branch of the S-curve is performed. Better agreement with experiments in terms of pressure oscillation amplitude is found when the full S-curve is used.

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Prediction of Combustion Instability with Detailed Chemical Kinetics

Cited by 36 publications

References 17 publications

Reduced-Order Modeling of Model Rocket Combustors

Reduced-Order Modeling of Model Rocket Combustors

Numerical issues in modeling combustion instability by quasi-1D Euler equations

The impacts of three flamelet burning regimes in nonlinear combustion dynamics

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