Computational Study of Combustor–Turbine Interactions

Miki, Kenji; Moder, Jeffrey P.; Liou, Meng-Sing

doi:10.2514/1.b36909

Cited by 15 publications

(20 citation statements)

References 38 publications

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“…In principle LES-LEM is better suited for these problems, but this capability remains to be demonstrated. Thus, future work on its development should consider test problems closer to actual applications, problems such as the high-Reynoldsnumber, premixed jet burner of Dunn et al [85], or the very-high-Reynolds-number, gasturbine-like LM6000 [86,87] or GE-E3 [88] combustors, and conduct careful comparisons with, say, the no-model approach at various levels of mesh refinement.…”

Section: Discussionmentioning

confidence: 99%

Subgrid Reaction-Diffusion Closure for Large Eddy Simulations Using the Linear-Eddy Model

Arshad

Gonzalez-Juez

Dasgupta

et al. 2019

Flow Turbulence Combust

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Turbulent combustion models approximate the interaction between turbulence, molecular transport and chemical reactions. Among the many available turbulent combustion models, the present focus is the linear-eddy model (LEM) used as a subgrid combustion model for large eddy simulations. In particular this paper introduces a new LEM closure with the reaction-rate approach to close the filtered chemical source terms in the governing equations for species mass fractions and enthalpy. The new approach is tested using a nonpremixed syngas flame and a bluff-body stabilized premixed flame problem. Simulation results are compared to data from a direct numerical simulation and experiments. This comparison shows that mean and rms quantities compare well with experiments and are in the range of previous simulation studies. These results are obtained with a pressure-based and unstructured computational-fluid-dynamics solver, an approach that is preferred in industry. Keywords Turbulent combustion model • Large eddy simulations • Linear-eddy model • Chemical source term closure • Bluff-body stabilized flame • Reacting temporal jet • Splicing

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Section: Discussionmentioning

confidence: 99%

Subgrid Reaction-Diffusion Closure for Large Eddy Simulations Using the Linear-Eddy Model

Arshad

Gonzalez-Juez

Dasgupta

et al. 2019

Flow Turbulence Combust

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“…The authors pointed out that SAS predicts better than RANS the recirculating region inside the combustor, which has a large impact over the resulting gas temperature at the turbine inlet and over the coolant and the main stream mixing process, even if it mildly affects the velocity field. As a matter of fact, even if RANS is sufficient to predict the aerodynamics of the turbine and to provide a reasonably accurate solution with a low computational effort [33], Scale-Resolving methods are required to assess satisfactorily the thermal behavior of the vanes, as demonstrated by subsequent works [34,35].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Combustor-Turbine Interaction by Using Hybrid RANS-LES Approach

Tomasello

Andreini

Meloni³

et al. 2022

Volume 6A: Heat Transfer — Combustors; Film Cooling

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The complex flow field of gas turbine lean combustors is meant to reduce NOx emissions and maintain a stable flame by controlling the local temperature and promoting high turbulent mixing. Still, this may produce large flow and temperature unsteady distortions capable of disrupting the aerodynamics and heat transfer of the first high-pressure-turbine cooled nozzle. Therefore, the interaction between the combustion chamber and the turbine nozzle is analyzed first with the help of scale-resolving simulations that notably also include a realistic turbine nozzle cooling system. To determine the nature and severity of the interaction, and the risks associated to performing decoupled simulation, the results of the coupled computer simulation are analyzed and compared with those of decoupled simulations. In this case, the combustor is computed by replacing the turbine nozzle with a discharge convergent with the same throat area, and the conditions at the interface plane are used as inlet boundary conditions for a conventional RANS of the nozzle. The analyses of the coupled and decoupled simulation reveal that the combustion chamber is weakly affected by the presence of the nozzle, whereas the two thermal fields of the nozzle surface differ considerably, as well as the disruption of the film cooling by the incoming flow distortions.

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“…Nonetheless, these approaches still lead to strong hypotheses on the information provided from one code to the other, implying approximations on the mass-flow rate, total energy and turbulent quantities. Using a single LES solver to solve the full system constitutes a high potential solution to avoid these approximations (Duchaine et al, 2017;Miki et al, 2018;Thomas et al, 2019;Miki et al, 2020). Such multi-component LES simulations for example accurately represent the critical unsteady high temperature spots issued from the combustion chamber that impact on the turbine blades.…”

Section: Introductionmentioning

confidence: 99%

Towards the Large-Eddy Simulation of a full engine: Integration of a 360 azimuthal degrees fan, compressor and combustion chamber. Part I: Methodology and initialisation

Arroyo

Dombard

Duchaine

et al. 2021

J. Glob. Power Propuls. Soc.

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Optimising the design of aviation propulsion systems using computational fluid dynamics is essential to increase their efficiency and reduce pollutant as well as noise emissions. Nowadays, and within this optimisation and design phase, it is possible to perform meaningful unsteady computations of the various components of a gas-turbine engine. However, these simulations are often carried out independently of each other and only share averaged quantities at the interfaces minimising the impact and interactions between components. In contrast to the current state-of-the-art, this work presents a 360 azimuthal degrees large-eddy simulation with over 2100 million cells of the DGEN-380 demonstrator engine enclosing a fully integrated fan, compressor and annular combustion chamber at take-off conditions as a first step towards a high-fidelity simulation of the full engine. In order to carry such a challenging simulation and reduce the computational cost, the initial solution is interpolated from stand-alone sectoral simulations of each component. In terms of approach, the integrated mesh is generated in several steps to solve potential machine dependent memory limitations. It is then observed that the 360 degrees computation converges to an operating point with less than 0.5% difference in zero-dimensional values compared to the stand-alone simulations yielding an overall performance within 1% of the designed thermodynamic cycle. With the presented methodology, convergence and azimuthally decorrelated results are achieved for the integrated simulation after only 6 fan revolutions.

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Computational Study of Combustor–Turbine Interactions

Cited by 15 publications

References 38 publications

Subgrid Reaction-Diffusion Closure for Large Eddy Simulations Using the Linear-Eddy Model

Subgrid Reaction-Diffusion Closure for Large Eddy Simulations Using the Linear-Eddy Model

Numerical Study of Combustor-Turbine Interaction by Using Hybrid RANS-LES Approach

Towards the Large-Eddy Simulation of a full engine: Integration of a 360 azimuthal degrees fan, compressor and combustion chamber. Part I: Methodology and initialisation

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