Simulation of rotating stall in a whole stage of an axial compressor

Gourdain, Nicolas; Burguburu, S.; Leboeuf, Francis; Michon, Guy-Jean

doi:10.1016/j.compfluid.2010.05.017

Cited by 54 publications

(41 citation statements)

References 22 publications

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“…Rotating stall is a local instability characterized by one or more cells of stalled flow which rotate around the compressor annulus at a fraction of the rotor speed. However, since the number of cells is not correlated to the number of blades or vanes, it requires a 360 • simulation [28][29][30] in simulations. Moreover, surge affects the whole compression system [31,32] (the whole engine in case of gas turbine configurations or the experimental facility in case of research compressor).…”

Section: Review Of Some Challengesmentioning

confidence: 99%

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: Review Of Some Challengesmentioning

confidence: 99%

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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“…Firstly, the two lower fluctuation frequency components of 0.31 BPF and 0.47 BPF both disappear due to the impact of the CT grooves. It has been found that the occurrence of the low dominating frequency components is linked to the rotating instabilities [47,48]. Therefore, the vanishing of the low frequency components may probably contribute to the delay of stall inception and the SMI.…”

Section: The Impact Of Cts On the Inside Unsteady Fluctuationsmentioning

confidence: 99%

Numerical Investigation for the Impact of Single Groove on the Stall Margin Improvement and the Unsteadiness of Tip Leakage Flow in a Counter-Rotating Axial Flow Compressor

Mao¹,

Liu²,

Zhao³

2017

Energies

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Abstract:A low-speed counter-rotating axial flow compressor (CRAC) with single circumferential grooved casing treatment (CT) was investigated numerically. Both steady and time-accurate numerical calculations were performed to study the effects of the single grooved CTs over the rear rotor on the stability enhancement and the unsteadiness of tip leakage flow (TLF) in the CRAC. Parametric studies indicate that the best position of the single groove should be located near about 20% axial tip chord in terms of the stall margin improvement (SMI). The coincidence of the effective CT locations and the high fluctuating region on blade pressure surface in the smooth wall case shows that the unsteadiness of TLF plays an important role in the stall inception process. Frequency analysis for the static pressure signals near the blade tip shows that both the disappearance of the low frequency components and the suppression of unsteady TLF are beneficial to the SMI. Detailed observation of the flow structures illustrates that the action of the grooves on the different parts of TLF is responsible for the difference of SMI in the CTs. It is more effective to improve the flow stability by controlling the critical TLF released from near the mid-chord.

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“…Therefore, an idealized throttle function is applied at the outlet of the fan. The static pressure at the outlet is determined by a quadratic law [9]:…”

Section: Throttle Modelmentioning

confidence: 99%

“…Meanwhile, some researchers have worked on the details of the flow field during stalls based on numerical simulations. Gourdain [8,9] numerically studied the rotating stall in a subsonic compressor, and discovered that stall cells are caused by the upstream flow disorganization and rotating stalls are initiated by an up-stream modal wave. Choi [10] found that the mis-staggered blade is instrumental to stall initiation because the increasing blade loading intensified the tip leakage flow to cause spillage around the leading edge of the trailing blade.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Entropy Generation under Stall Conditions in a Centrifugal Fan

Zhang

Lang

Jiang

et al. 2014

Entropy

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Rotating stalls are generally the first instability met in turbomachinery, before surges. This 3D phenomenon is characterized by one or more stalled flow cells which rotate at a fraction of the impeller speed. The goal of the present work is to shed some light on the entropy generation in a centrifugal fan under rotating stall conditions. A numerical simulation of entropy generation is carried out with the ANSYS Fluent software which solves the Navier-Stokes equations and user defined function (UDF). The entropy generation characteristics in the centrifugal fan for five typical conditions are presented and discussed, involving the design condition, conditions on occurrence and development of stall inception, the rotating stall conditions with two throttle coefficients. The results show that the entropy generation increases after the occurrence of stall inception. The high entropy generation areas move along the circumferential and axial directions, and finally merge into one stall cell. The entropy generation rate during circumferential propagation of the stall cell is also discussed, showing that the entropy generation history is similar to sine curves in impeller and volute, and the volute tongue has a great influence on entropy generation in the centrifugal fan.

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Simulation of rotating stall in a whole stage of an axial compressor

Cited by 54 publications

References 22 publications

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

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

Numerical Investigation for the Impact of Single Groove on the Stall Margin Improvement and the Unsteadiness of Tip Leakage Flow in a Counter-Rotating Axial Flow Compressor

Simulation of Entropy Generation under Stall Conditions in a Centrifugal Fan

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