FENSAP-ICE: Modeling of Water Droplets and Ice Crystals

Habashi, Wagdi G.; Aubé, Martin S.; Baruzzi, Guido S.

doi:10.2514/6.2009-4128

Cited by 18 publications

(10 citation statements)

References 10 publications

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“…Thus, ice accretion phenomena are a serious problem in aircraft operations. In order to overcome the problems associated with icing, a number of major research institutes around the world, including NASA (National Aeronautics and Space Administration) and ONERA (Office National d'Etudes et de Recherches Aerospatiales) have been investigating ice accretion phenomena both experimentally and computationally [1][2][3][4].…”

Section: Numerical Simulation On Ice Shedding Phenomena In Turbomachimentioning

confidence: 99%

Numerical Simulation on Ice Shedding Phenomena in Turbomachinery

Hayashi¹,

Yamamoto²

2015

JEPE

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Abstract:In the jet engine, icing phenomena occur primarily on the fan blades, the FEGVs (fan exit guide vanes), the splitter, and the low-pressure compressor. Accreted ice disturbs the inlet flow and causes large energy losses. In addition, ice accreted on a fan rotor can be shed from the blade surface due to centrifugal force and can damage compressor components. This phenomenon, which is typical in turbomachinery, is referred to as ice shedding. Although existing icing models can simulate ice growth, these models do not have the capability to reproduce ice shedding. In the present study, we develop an icing model that takes into account both ice growth and ice shedding. Furthermore, we have validated the proposed ice shedding model through the comparison of numerical results and experimental data, which include the flow rate loss due to ice growth and the flow rate recovery due to ice shedding. The simulation results for the time at which ice shedding occurred and what were obtained using the proposed ice shedding model were in good agreement with the experimental results.

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Section: Numerical Simulation On Ice Shedding Phenomena In Turbomachimentioning

confidence: 99%

Numerical Simulation on Ice Shedding Phenomena in Turbomachinery

Hayashi¹,

Yamamoto²

2015

JEPE

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“…The grid module is designed to generate a perfect grid system automatically around the model and redefine the iced geometry [7] . During generating the grid system, this module can generate a discrete approximation to the surface as faithfully as possible for a given number of points.…”

Section: B Module Of Grid Generation and Reconstructionmentioning

confidence: 99%

Development and Validation of Aircraft Icing Computational Simulation Code

Zhu

Guo

et al. 2015

Proceedings of the 2nd International Conference on Intelligent Computing and Cognitive Informatics

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The purpose of this paper is to present some results on the development and verification of NUAA-ICE2D icing software code, which contains five separate program modules and a graphical user interface. Computational simulation of the ice accretion process on airfoils using multiple time-steps is studied in this paper. Firstly, all the modular codes for icing computation have been established in FORTRAN90 based on the Dynamic Link Library (DLL), and then a software package to perform normal functions of these modules has been developed using Microsoft Foundation Classes (MFC) framework. In addition, this icing software has some visualization tools that can help user analyze, explore and understand the simulation data. The architecture of the software, the functions of each component, its application to icing prediction and the further development are also discussed in this document. It is shown that all the modular codes of the software have good precision and fast calculation velocity during the process of grid generation, flow field calculation, droplet impingement calculation and ice growth analysis because of use of DLL and MFC, the illustration chart of operational interface is briefly shown in Figure 1. This platform software not only has established a reliable data communications law among these computational modules, but also has given an efficient way to predict the ice-layer accretion on the surfaces of geometry, the results are compared we are in accordance with the experimental data, shown in Figure 2. Once the calculations for ice accretion are activated, the software can call the five modules alternately and automatically in a robust way. This paper will provide some new techniques for predicting the ice accretion on airfoil efficiently and developing integrated icing software using mixed-language programming, which can be used in the stage of airfoil design and assessment. This paper presents some new ideas to improve the efficiency and reliability in icing calculations, especially in user-oriented way.

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“…航空機が運航する高度の雲の中には，過冷却液滴が多く存在することがある．雲中の過冷却液滴は，機体などに衝突すると凍結し，衝突面に氷層を形成する．これを着氷現象と呼ぶ．着氷は，主翼においては翼性能の低下やストール，エンジンにおいては作動効率低下の要因となるため，安全な航空機運航の妨げとなり，事実，着氷による航空機事故が世界各地で発生している (Isaac, et al, 2001) ．この問題を解決するために，着氷現象に関する研究は，NASA をはじめとする世界的に主要な機関において，実験と数値解析の両方の側面から長く行われている (Wright, et al, 1997, Nilamdeen and Habashi, 2009, Presteau, et al, 2009, Veres, et al, 2011 (Ozgen and Canıbek, 2009, Hospers and Hoeijmakers, 2011, Aliaga, et al, 2011, Hayashi, et al, 2011 ．主翼・尾翼の着氷に関しては，古くから研究されており，breed air や de-icer boots などをはじめとする防氷・除氷技術の対策も講じられている．しかし，エンジン着氷において現状では，実用的な防氷・除氷装置は完備されていない．ジェットエンジンの主な着氷箇所は，スピナ，スプリッタ，ファン動翼，バイパス出口案内翼，低圧コンプレッサである．また，近年では高圧コンプレッサなどのエンジンコアにおける着氷発生事例もあり，エンジン着氷に対する研究が盛んに進められている (Jeanne, et al, 2006, Veillard and) ．着氷現象に付随する現象に氷の離脱現象がある．ジェットエンジンの場合には，ファンに堆積した氷が成長し，高速で回転しているファンの遠心力により翼表面から氷が剥がれ落ちる．離脱した氷片はエンジンコアに吸い込まれ，コアコンポーネントに損傷を与える．本現象は，大気中の氷の密度，氷と壁面の付着力，氷と氷の接触力など，氷の物性値には不明な点が多く，非常に複雑である．Papadakis ら (Papadakis, et al, 2007)は，氷片を模擬した長方形平板にかかる力とモーメント係数を風洞設備で測定し，得られた空力データを用い主翼から飛散する氷片の追跡計算を行った．また，Baruzzi ら (Baruzzi, et al, 2007)…”

Section: 緒言unclassified

Modelling of ice shedding phenomenon for engine fan icing

Hayashi

Yamamoto

2014

Transactions of the JSME (In Japanese)

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In a jet engine, icing phenomena may occur primarily on the fan blades, the fan exit guide vanes (FEGVs), the splitter, and the low-pressure compressor. Accreted ice disturbs the inlet flow and causes large energy losses. In addition, ice accreted on a fan rotor can be shed from the blade surface due to centrifugal force and can damage the compressor components. This phenomenon, which is typical in turbomachinery, is referred to as ice shedding. The ice shedding phenomenon is very complicated because there are several unknown physical properties of ice, such as the ice density, the adhesion force between accreted ice and the wall, and the contact force between ice pieces. Moreover, although existing icing models can simulate ice growth, these models do not have the capability to reproduce ice shedding. In the present study, we developed an icing model that takes into account both ice growth and ice shedding. We validated the proposed ice shedding model through the comparison of numerical results and experimental data, which includes the flow rate loss due to ice growth and the flow rate recovery due to ice shedding. The predictive shedding time obtained using the proposed ice shedding model were in good agreement with the experimental data. Finally, we investigated the effects of ice growth and ice shedding on the fan performance.

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FENSAP-ICE: Modeling of Water Droplets and Ice Crystals

Cited by 18 publications

References 10 publications

Numerical Simulation on Ice Shedding Phenomena in Turbomachinery

Numerical Simulation on Ice Shedding Phenomena in Turbomachinery

Development and Validation of Aircraft Icing Computational Simulation Code

Modelling of ice shedding phenomenon for engine fan icing

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