Large Eddy Simulation of Combustor and Complete Single-Stage High-Pressure Turbine of the FACTOR Test Rig

Thomas, Martin; Dombard, Jérôme; Duchaine, Florent; Gicquel, Laurent; Koupper, Charlie

doi:10.1115/gt2019-91206

Cited by 6 publications

(4 citation statements)

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“…It is also relevant to underline that [170] demonstrated by means of integrated LES of the combustor simulator and the high-pressure vane that the potential effect induced by the vanes altered the mass flow rate redistribution and the turbulence level at the turbine inlet section, even though the temperature pattern was mostly unaltered. Recently, [179] performed integrated LES of the combustor simulator and of the high-pressure turbine stage, thus demonstrating its feasibility at academic and industrial levels. However, open issues remain and highorder numerical schemes as well as adaptive grid refinement may help understand some discrepancies between experiments and simulations, which are probably caused by coolant injection model and secondary flow development.…”

Section: Combustor Simulators For Combustor/turbine Interaction Analysismentioning

confidence: 99%

Unsteady Flows and Component Interaction in Turbomachinery

Salvadori,

Insinna,

Martelli

2024

IJTPP

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Unsteady component interaction represents a crucial topic in turbomachinery design and analysis. Combustor/turbine interaction is one of the most widely studied topics both using experimental and numerical methods due to the risk of failure of high-pressure turbine blades by unexpected deviation of hot flow trajectory and local heat transfer characteristics. Compressor/combustor interaction is also of interest since it has been demonstrated that, under certain conditions, a non-uniform flow field feeds the primary zone of the combustor where the high-pressure compressor blade passing frequency can be clearly individuated. At the integral scale, the relative motion between vanes and blades in compressor and turbine stages governs the aerothermal performance of the gas turbine, especially in the presence of shocks. At the inertial scale, high turbulence levels generated in the combustion chamber govern wall heat transfer in the high-pressure turbine stage, and wakes generated by low-pressure turbine vanes interact with separation bubbles at low-Reynolds conditions by suppressing them. The necessity to correctly analyze these phenomena obliges the scientific community, the industry, and public funding bodies to cooperate and continuously build new test rigs equipped with highly accurate instrumentation to account for real machine effects. In computational fluid dynamics, researchers developed fast and reliable methods to analyze unsteady blade-row interaction in the case of uneven blade count conditions as well as component interaction by using different closures for turbulence in each domain using high-performance computing. This research effort results in countless publications that contribute to unveiling the actual behavior of turbomachinery flow. However, the great number of publications also results in fragmented information that risks being useless in a practical situation. Therefore, it is useful to collect the most relevant outcomes and derive general conclusions that may help the design of next-gen turbomachines. In fact, the necessity to meet the emission limits defined by the Paris agreement in 2015 obliges the turbomachinery community to consider revolutionary cycles in which component interaction plays a crucial role. In the present paper, the authors try to summarize almost 40 years of experimental and numerical research in the component interaction field, aiming at both providing a comprehensive overview and defining the most relevant conclusions obtained in this demanding research field.

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Section: Combustor Simulators For Combustor/turbine Interaction Analysismentioning

confidence: 99%

Unsteady Flows and Component Interaction in Turbomachinery

Salvadori,

Insinna,

Martelli

2024

IJTPP

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“…In this context, a valid and more reliable alternative to RANS is represented by a large-eddy simulation (LES) [27][28][29], since it is able to resolve most of the turbulence scales and, thus, to provide high-fidelity solutions [30]. However, the employment of LES modeling results in a very high required computational cost due to the strict spatial and temporal discretization required.…”

Section: Introductionmentioning

confidence: 99%

Study of Combustor–Turbine Interactions by Performing Coupled and Decoupled Hybrid RANS-LES Simulations under Representative Engine-like Conditions

Tomasello¹,

Meloni²,

Andrei³

et al. 2023

Energies

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Combustion–turbine interaction phenomena are attracting ever-growing interest in recent years. As a matter of fact, the strong unsteady and three-dimensional flow field that characterizes the combustor is usually conserved up to the first-stage nozzle, possibly affecting its design and performance in terms of aerodynamics and the effectiveness of the cooling system as well. Such conditions are also exacerbated by the employment of lean-burn combustors, where high turbulence levels are required for the flame stabilization, resulting in even greater temperature and velocity distortions at the inlet of the first-stage nozzle. Even if it has been proven by several past studies that the best way of studying the combustor–turbine interaction is simulating the two components together, performing coupled simulations is still challenging from a numerical point of view, especially in an industrial context. For this reason, the application and generation of the most representative and reliable boundary conditions possible at the inlet of the S1N have assumed an increased importance in order to study the two components separately by performing decoupled simulations. In this context, the purpose of the present work is to compare fully integrated combustor–stator SBES simulations to isolated stator ones. To perform the stator-only calculations, the fully unsteady inlet conditions of the stator have been recorded at the interface plane between the two components in the integrated SBES simulation and then they have been reconstructed by applying the proper orthogonal decomposition (POD) technique. The SBES simulations of the isolated stator have been so performed with the aim of determining whether the flow field obtained is comparable with the one of the integrated simulation, thus allowing more realistic results to be obtained rather than imposing time-averaged 2D maps, as per standard design practice.

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“…A valid alternative is represented by Large-Eddy Simulation (LES), which resolves the majority of the turbulent flow structures and models fine scale dissipative structures [22]. However, although its application for the study of the combustorturbine interaction has been recently documented [23][24][25] and it has been applied also for industrial purpose [26], it is usually employed for simplified laboratory geometries due to the high computational effort required. Moreover, film cooling holes are generally neglected.…”

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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Large Eddy Simulation of Combustor and Complete Single-Stage High-Pressure Turbine of the FACTOR Test Rig

Cited by 6 publications

References 0 publications

Unsteady Flows and Component Interaction in Turbomachinery

Unsteady Flows and Component Interaction in Turbomachinery

Study of Combustor–Turbine Interactions by Performing Coupled and Decoupled Hybrid RANS-LES Simulations under Representative Engine-like Conditions

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

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