Comparison of Heterogeneous and Homogeneous Coolant Injection Models for Large Eddy Simulation of Multiperforated Liners Present in a Combustion Simulator

Thomas, Martin; Dauptain, Antoine; Duchaine, Florent; Gicquel, Laurent; Koupper, Charlie; Nicoud, Franck

doi:10.1115/gt2017-64622

Cited by 4 publications

(3 citation statements)

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“…Andreini et al [176] also confirmed that the adiabatic homogeneous model by Mendez and Nicoud [177] allowed for accounting for the presence of effusion cooling with coarse grids, even if some limitations in reproducing the film temperature were found. Thomas et al [178] simulated the same test case using a newly developed heterogeneous model for effusion cooling, concluding that it led to similar results as the validated homogeneous injection model. 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.…”

Section: Combustor Simulators For Combustor/turbine Interaction Analysismentioning

confidence: 79%

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: 79%

Unsteady Flows and Component Interaction in Turbomachinery

Salvadori,

Insinna,

Martelli

2024

IJTPP

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“…Indeed, with the thickened-hole model, from a unique mesh of an engine, many hole layouts can be tested: "One mesh fits all". This methodology was recently used in the design of a real engines [28][29][30].…”

Section: Resultsmentioning

confidence: 99%

A Thickened-Hole Model for Large Eddy Simulations over Multiperforated Liners

Bizzari

Lahbib

Dauptain

et al. 2018

Flow Turbulence Combust

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In aero-engines, mutiperforation cooling systems are often used to shield the combustor wall and ensure durability of the engine. Fresh air coming from the casing goes through thousands of angled perforations and forms a film which protects the liner. When performing Large Eddy Simulations (LES) of a real engine, the number of sub-millimetric holes is far too large to allow a complete and accurate description of each aperture. Homogeneous models allow to simulate multiperforated plates with a mesh size bigger than the hole but fail in representing the jet penetration and mixing. A heterogeneous approach is proposed in this study, where the apertures are thickened if necessary so that the jet-crossflow interaction is properly represented. Simulations using homogeneous and thickened-hole models are compared to a fully resolved computation for various grid resolutions in order to illustrate the potential of the method.

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“…Furthermore, due to the rotational motion induced by the fuel injection system, the combustion chamber outlet exhibits a high level of turbulence (with a turbulence intensity of 20%) and a residual swirling motion, as well as flow and temperature nonuniformities [21,22]. The multiperforations which protect the combustor walls from the high temperatures of the chamber also play an important role in the flow dynamics [23,24]. All of these characteristics partly explain why it is difficult to perform simulations of isolated high-pressure turbines with realistic boundary conditions.…”

Section: Combustion Chamber/turbine Integrated Simulationmentioning

confidence: 99%

Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation

et al. 2021

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Numerical simulation of multiple components in turbomachinery applications is very CPU-demanding but remains necessary in the majority of cases to capture the proper coupling and a reliable flow prediction. During a design phase, the cost of simulation is, however, an important criterion which often defines the numerical methods to be used. In this context, the use of realistic boundary conditions capable of accurately reproducing the coupling between components is of great interest. With this in mind, this paper presents a method able to generate more realistic boundary conditions for isolated turbine large-eddy simulation (LES) while exploiting an available integrated combustion chamber/turbine LES. The unsteady boundary conditions to be used at the inflow of the isolated turbine LES are built from the modal decomposition of the database recorded at the interface between the two components of the integrated LES simulation. Given the reference LES database, the reconstructed field boundary conditions can then be compared to standard boundary conditions in the case of isolated turbine configuration flow predictions to illustrate the impact. The results demonstrate the capacity of this type of conditions to reproduce the coupling between the combustion chamber and the turbine when standard conditions cannot. The aerothermal predictions of the blade are, in particular, very satisfactory, which constitutes an important criterion for the adoption of such a method during a design phase.

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Comparison of Heterogeneous and Homogeneous Coolant Injection Models for Large Eddy Simulation of Multiperforated Liners Present in a Combustion Simulator

Cited by 4 publications

References 0 publications

Unsteady Flows and Component Interaction in Turbomachinery

Unsteady Flows and Component Interaction in Turbomachinery

A Thickened-Hole Model for Large Eddy Simulations over Multiperforated Liners

Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation

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