Towards Large Eddy Simulation of gas turbine compressors

McMullan, W. A.; Page, Gary J.

doi:10.1016/j.paerosci.2011.12.002

Cited by 33 publications

(32 citation statements)

References 41 publications

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“…Using LES alone will limit the increase in CFD accuracy, owing to real geometry effects [2]. The use of LES with unstructured meshes allows one to take into account more complex geometry and fluid flow interactions in compressor applications [6]. This approach is also well suited to high-performance computing requirements (load balancing, reduction of MPI size messages, etc.).…”

Section: (B) Towards Real Geometrymentioning

confidence: 99%

Section: Current Research Workmentioning

confidence: 99%

“…However, an accurate description of the flow at the inlet plane is also mandatory to achieve a correct accuracy. In that regard, the lack of experimental data (such as turbulent intensity and spectrum) is often reported in the literature [6,12,61] as a major source of uncertainty to validate LES results. Another difficulty is related to the definition of boundary conditions at walls.…”

Section: (C) Boundary Conditionsmentioning

confidence: 99%

“…The most popular approach for the mesh generation relies on structured grids but these works usually consider academic configurations (isolated blade profile or simplified compressor geometry). The use of unstructured grids is preferred for complex geometries close to industrial configurations [6,59].Most works consider grids which are far from academic recommendations for wall-resolved LES: x + < 100, y+ < 1 and z+ < 20 [51]. Indeed, most studies deal with under-resolved LES, especially in the near-wall region.…”

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confidence: 99%

“…However, the rotation and curvature effects encountered in compressors are responsible for a modification of the near-wall flow that should be taken into account in wall modelling, as suggested in [71,72]. At least, a proper validation of wall modelling in compressors can be performed against wall-resolved LES, already available [6,25].The phaselag conditions developed by Erdos et al [73] allow to solve for only one blade passage per row, reducing drastically the mesh size. By periodically storing the flow field (e.g.…”

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confidence: 99%

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Large eddy simulation of flows in industrial compressors: a path from 2015 to 2035

Gourdain

Sicot

Duchaine

et al. 2014

Phil. Trans. R. Soc. A.

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One contribution of 13 to a Theme Issue 'Aerodynamics, computers and the environment' . A better understanding of turbulent unsteady flows is a necessary step towards a breakthrough in the design of modern compressors. Owing to high Reynolds numbers and very complex geometry, the flow that develops in such industrial machines is extremely hard to predict. At this time, the most popular method to simulate these flows is still based on a Reynoldsaveraged Navier-Stokes approach. However, there is some evidence that this formalism is not accurate for these components, especially when a description of time-dependent turbulent flows is desired. With the increase in computing power, large eddy simulation (LES) emerges as a promising technique to improve both knowledge of complex physics and reliability of flow solver predictions. The objective of the paper is thus to give an overview of the current status of LES for industrial compressor flows as well as to propose future research axes regarding the use of LES for compressor design. While the use of wallresolved LES for industrial multistage compressors at realistic Reynolds number should not be ready before 2035, some possibilities exist to reduce the cost of LES, such as wall modelling and the adaptation of the phase-lag condition. This paper also points out the necessity to combine LES to techniques able to tackle complex geometries. Indeed LES alone, i.e. without prior knowledge of such flows for grid construction or the prohibitive yet ideal use of fully homogeneous meshes to predict compressor flows, is quite limited today. IntroductionThe aeronautic industry faces a formidable challenge by targeting in 2050 a reduction of CO 2 and NO x 2014 The Author(s) Published by the Royal Society. All rights reserved. emissions by 75% and 90% per kilometre and per passenger, respectively (compared to the 2000 level). Ultra-high bypass ratio (BR > 20) turbofan and ultra-high overall pressure ratio (OPR > 70) core engines have the potential for such significant reductions in fuel burn. However, after many years of optimization, the design of ever more efficient gas turbines now requires understanding of the complex unsteady flow appearing within each individual component and in an integrated fashion. Among all components, the compressor remains a critical part of a gas turbine, especially regarding its efficiency and stability. Owing to the adverse pressure gradients, compressors are naturally subjected to unstable flows such as surge and rotating stall [1], which can potentially lead to mechanical failure. These aerodynamic instabilities impose serious constraints on the design (the so-called 'surge margin') and thus on performance. In this context, maximizing the efficiency of compressors remains particularly complex and the improvement of the compressor robustness and performance thus requires good understanding of the flow physics.Complementary to experimental investigations, the numerical simulation of flows, commonly referred to as computational fluid dynamics (CFD), is...

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Section: (B) Towards Real Geometrymentioning

confidence: 99%

Section: Current Research Workmentioning

confidence: 99%

Section: (C) Boundary Conditionsmentioning

confidence: 99%

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confidence: 99%

mentioning

confidence: 99%

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Large eddy simulation of flows in industrial compressors: a path from 2015 to 2035

Gourdain

Sicot

Duchaine

et al. 2014

Phil. Trans. R. Soc. A.

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Wall-Modeled Large-Eddy Simulations of a Multistage High-Pressure Compressor

Laborderie

Duchaine

Gicquel

et al. 2019

Flow Turbulence Combust

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This study aims at evaluating the feasibility and the accuracy of a Wall-Modeled Large Eddy Simulation of an actual aeronautical multistage axial high-pressure compressor. The computational domain is composed of 37 blades and a geometrically complex recirculating cavity. The numerical method TurboAVBP is able to handle such a technical challenge thanks to its unstructured and massively parallel approach as well as dedicated rotor-stator interface treatments. The influence of grid resolution, from less than 100 millions to more than 1 billion of cells, is particularly evaluated. The intermediate grid correctly predicts the global aerodynamic performances up to the lowest mass flow rate regime. In comparing with time-resolved measurements, the finest grid is shown to accurately predict flow within rotors, especially in their tip regions that are critical for performances and stability of the whole compressor.

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