Description and assessment of the new ONERA 2D icing suite IGLOO2D

Trontin, Pierre; Blanchard, Ghislain; Kontogiannis, Alexandros; Villedieu, Philippe

doi:10.2514/6.2017-3417

Cited by 59 publications

(62 citation statements)

References 31 publications

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“…Ice accretion simulation on the first vane stage is performed using the IGLOO2D icing suite [12]. This numerical tool integrates several solver that can be used for the different phase of the calculation (see Fig.…”

Section: A Numerical Approachmentioning

confidence: 99%

Experimental characterization of anti-icing system and accretion of re-emitted droplets on turbojet engine blades

Linassier

Balland

Pervier

et al. 2018

2018 Atmospheric and Space Environments Conference

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In the framework of STORM, a European project dedicated to icing physics in aircraft engines, a cascade rig representative of an anti-iced engine inlet was tested in icing conditions. This mock-up integrates two rows of vanes, the upstream one being anti-iced using an Electro-Thermal Ice Protection System (ET-IPS). Experimental tests were performed to reproduce the following phenomena: runback water and droplet re-emission from anti-iced vanes, and accretion of re-emitted droplets on downstream vanes. A complete experimental database was generated, including the characterization of ice accretion shapes, and the characterization of electro-thermal anti-icing system (power limit for apparition of the runback water or ice accretion). In the current study, these data are compared to droplet trajectory simulation and ice accretion simulation results, for validating icing tools in engine environment. Influence of one-step and multi-step approaches have been investigated.

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Section: A Numerical Approachmentioning

confidence: 99%

Experimental characterization of anti-icing system and accretion of re-emitted droplets on turbojet engine blades

Linassier

Balland

Pervier

et al. 2018

2018 Atmospheric and Space Environments Conference

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“…Rough-wall criteria will not be employed for the present paper because roughness models are not addressed. However, it must be noted that most authors use the criterion Re k > 600, where Re k is a Reynolds number based on the roughness height k, for icing applications (LEWICE [2], IGLOO [4]). The criterion Re k > 600 will thus be a first step towards realistic rough-ice surface modelling in subsequent papers.…”

Section: Transition Criterionmentioning

confidence: 99%

“…First simulations over iced airfoils are presented in this section in order to show the capabilities of the method to perform calculations over complex geometries. The icing suite used to perform the ice accretion calculations is IGLOO2D [4]. Figure 18 illustrates the predictor ice shape obtained for the two sets of external conditions detailed in table 7.…”

Section: Glc305 Casesmentioning

confidence: 99%

“…For these reasons, the development of a general and robust 3D integral boundary layer Finite-aeronautic industry with efficient tools for icing applications. This opinion also relies on the fact that today, even for 2D computations, many existing icing tools (LEWICE [2], ONICE [3], IGLOO [4]) use simplified integral boundary layer models, such as the well-known method of Thwaites [5], and nevertheless are able to provide satisfactory results for most icing conditions. However, the 3D extension of these simplified boundary layer models is not straightforward since the formulation on which they are based is only two-dimensional.…”

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confidence: 99%

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Theory and validation of a 2D Finite-Volume integral boundary layer method intended for icing applications

Bayeux¹,

Radenac²,

Villedieu³

2017

47th AIAA Fluid Dynamics Conference

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“…This may result in engine stall, flameout or even engine damage. Contrary to aircraft icing caused by supercooled (large) droplets for which advanced prediction tools such as LEWICE [2], FENSAP-ICE [3,4] and ONICE [5,6] are currently available, ice accretion due to ice crystals is not yet fully understood.…”

mentioning

confidence: 99%

Eulerian and Lagrangian Ice-Crystal Trajectory Simulations in a Generic Turbofan Compressor

Norde

Senoner

Weide

et al. 2019

Journal of Propulsion and Power

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This study provides a comparison between an Eulerian and a Lagrangian approach for simulation of ice crystal trajectories and impact in a generic turbofan compressor. The engine-like geometry consists of a one-and-a-half stage (stator-rotor-stator) compressor in which the computed air flow is steady and inviscid. Both methods apply the same models to evaluate ice crystal dynamics, mass and heat transfer, and phase change along ice crystal trajectories. The impingement of the crystals on the blade surfaces is modeled assuming full deposition for comparison and validation purposes. Moreover, the effect of ice crystal diameter and sphericity variations on impinging mass flux and a

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Description and assessment of the new ONERA 2D icing suite IGLOO2D

Cited by 59 publications

References 31 publications

Experimental characterization of anti-icing system and accretion of re-emitted droplets on turbojet engine blades

Experimental characterization of anti-icing system and accretion of re-emitted droplets on turbojet engine blades

Theory and validation of a 2D Finite-Volume integral boundary layer method intended for icing applications

Eulerian and Lagrangian Ice-Crystal Trajectory Simulations in a Generic Turbofan Compressor

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