Large-Eddy Simulation of a Model Aero-Engine Sooting Flame With a Multiphysics Approach

Paccati, Simone; Bertini, Davide; Mazzei, Lorenzo; Puggelli, Stefano; Andreini, Antonio

doi:10.1007/s10494-020-00202-5

Cited by 11 publications

(9 citation statements)

References 22 publications

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“…A grid studies did not affect these differences [10]. Accordingly, the overestimated opening angle at h = 18 mm is observed in many other numerical publications [10,24,26,72], too. In conclusion, simulated and measured velocity profiles agree well within measurement uncertainties.…”

Section: Flow Fieldmentioning

confidence: 51%

“…The studied sooting aero-engine model combustor has been extensively investigated experimentally [4,5,9,[11][12][13][14] and is part of the ISF turbulent flame database [15]. Thanks to the large validation database, many numerical studies of this test case have been conducted for model validation [8,[16][17][18][19][20][21][22][23][24][25][26][27] or to analyze the sooting behavior [6,7,10,28]. LES was found to be necessary to properly simulate soot in this combustor [26].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Influence of operating conditions on flow field dynamics and soot formation in an aero-engine model combustor

Grader

Gerlinger

2023

Combustion and Flame

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Section: Flow Fieldmentioning

confidence: 51%

Section: Introductionmentioning

confidence: 99%

Influence of operating conditions on flow field dynamics and soot formation in an aero-engine model combustor

Grader

Gerlinger

2023

Combustion and Flame

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“…On the other hand, when the wall behaves as a semi-transparent medium, more accurate approaches can be adopted to improve the prediction of the radiative problem, as in Reference [ 28 ]. However, as demonstrated in Reference [ 29 ], when the Conjugate Heat Transfer is dominated by convection, the error neglecting wavelength dependency of radiative properties is minimum. As shown in Figure 1 , return quantity from the solid is the wall temperature, used as a mixed Dirichlet-Robin BC by flow and radiative field computations.…”

Section: Description Of Proposed Methodologymentioning

confidence: 99%

Prediction of Liner Metal Temperature of an Aeroengine Combustor with Multi-Physics Scale-Resolving CFD

Bertini

Mazzei

Andreini

2021

Entropy

Self Cite

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Computational Fluid Dynamics is a fundamental tool to simulate the flow field and the multi-physics nature of the phenomena involved in gas turbine combustors, supporting their design since the very preliminary phases. Standard steady state RANS turbulence models provide a reasonable prediction, despite some well-known limitations in reproducing the turbulent mixing in highly unsteady flows. Their affordable cost is ideal in the preliminary design steps, whereas, in the detailed phase of the design process, turbulence scale-resolving methods (such as LES or similar approaches) can be preferred to significantly improve the accuracy. Despite that, in dealing with multi-physics and multi-scale problems, as for Conjugate Heat Transfer (CHT) in presence of radiation, transient approaches are not always affordable and appropriate numerical treatments are necessary to properly account for the huge range of characteristics scales in space and time that occur when turbulence is resolved and heat conduction is simulated contextually. The present work describes an innovative methodology to perform CHT simulations accounting for multi-physics and multi-scale problems. Such methodology, named U-THERM3D, is applied for the metal temperature prediction of an annular aeroengine lean burn combustor. The theoretical formulations of the tool are described, together with its numerical implementation in the commercial CFD code ANSYS Fluent. The proposed approach is based on a time de-synchronization of the involved time dependent physics permitting to significantly speed up the calculation with respect to fully coupled strategy, preserving at the same time the effect of unsteady heat transfer on the final time averaged predicted metal temperature. The results of some preliminary assessment tests of its consistency and accuracy are reported before showing its exploitation on the real combustor. The results are compared against steady-state calculations and experimental data obtained by full annular tests at real scale conditions. The work confirms the importance of high-fidelity CFD approaches for the aerothermal prediction of liner metal temperature.

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“…The challenge in the application of the LES method is that it is computationally expensive and time-consuming, and application studies have not yet been sufficiently conducted. Recently, in the midst of active research to solve these challenges, Paccati et al (2021) used U-THERM3D, a multi physics unsteady approach, to reduce the simulation time in the LES of sooting-flame in a combustor. Experimental and numerical soot volume fraction distributions in the midplane of the combustor obtained by Paccati et al are shown in Figure 10.…”

Section: D Performance Evaluationmentioning

confidence: 99%

Design methodology for combustor in advanced gas turbine engines: a review

Kim,

Jin,

et al. 2024

AEAT

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Purpose A combustor design is a particularly important and difficult task in the development of gas turbine engines. During studies for accurate and easy combustor design, reasonable design methodologies have been established and used in engine development. The purpose of this paper is to review the design methodology for combustor in development of advanced gas turbine engines. The advanced combustor development task can be successfully achieved in less time and at lower cost by adopting new and superior design methodologies. Design/methodology/approach The review considers the main technical problems (combustion, cooling, fuel injection and ignition technology) in the development of modern combustor design and deals with combustor design methods by dividing it into preliminary design, performance evaluation, optimization and experiment. The advanced combustion and cooling technologies mainly used in combustor design are mentioned in detail. In accordance with the modern combustor design method, the design mechanisms are considered and the methods used in every stage of the design are reviewed technically. Findings The improved performances and strict emission limits of gas turbine engines require the application of advanced technologies when designing combustors. The optimized design mechanism and reasonable performance evaluation methods are very important in reducing experiments and increasing the effectiveness of the design. Originality/value This paper provides a comprehensive review of the design methodology for the advanced gas turbine engine combustor.

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Large-Eddy Simulation of a Model Aero-Engine Sooting Flame With a Multiphysics Approach

Cited by 11 publications

References 22 publications

Influence of operating conditions on flow field dynamics and soot formation in an aero-engine model combustor

Influence of operating conditions on flow field dynamics and soot formation in an aero-engine model combustor

Prediction of Liner Metal Temperature of an Aeroengine Combustor with Multi-Physics Scale-Resolving CFD

Design methodology for combustor in advanced gas turbine engines: a review

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