In-flight Icing: Modeling, Prediction, and Uncertainty

Arizmendi, B.; Morelli, Myles; Parma, Gianluca; Zocca, Marta; Quaranta, Giuseppe; Guardone, Alberto

doi:10.1007/978-3-030-60166-9_15

Cited by 3 publications

(3 citation statements)

References 73 publications

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“…Finally, it may be interesting to take into account the high degree of uncertainty inherent to icing in aeronautics. Some research efforts have already been performed in this direction [55,56] and are the subject of ongoing investigations. For the simulations, several meshes were used.…”

Section: Discussionmentioning

confidence: 99%

Numerical Simulation of an Electrothermal Ice Protection System in Anti-Icing and Deicing Mode

2023

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The design of efficient thermal ice protection systems is a challenging task as these systems operate in complex environments involving several coupled physical phenomena such as phase change, boundary-layer flow, and heat transfer. Moreover, certification rules are becoming more stringent, and there is a strong incentive for the reduction of fuel consumption. In this context, numerical tools provide a powerful asset during the design phase but also to gain insight into the physical mechanisms at play. This article presents modeling and simulation strategies for thermal ice protection systems. First, the model describing the behavior of the thermal protection system is presented. Second, a model and associated numerical method is presented for unsteady ice accretion. Third, the coupling methodology between the ice accretion solver and the heat conduction solver is described. In the fourth part, different methods to simulate the boundary-layer flow are described. Finally, some relevant examples are presented, both in steady and unsteady configurations.

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Section: Discussionmentioning

confidence: 99%

Numerical Simulation of an Electrothermal Ice Protection System in Anti-Icing and Deicing Mode

2023

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“…At temperatures below freezing, water may still remain liquid, as supercooled droplets. This state is unstable and these droplets may freeze abruptly when coming in contact with a solid surface [ 9 ]. The obstruction of one or more of the pressure ports in a probe can lead to the corruption of the system readings [ 10 ].…”

Section: Introductionmentioning

confidence: 99%

“…The obstruction of one or more of the pressure ports in a probe can lead to the corruption of the system readings [ 10 ]. The normally chosen Icing Protection System (IPS) used to protect this type of system is thermo-electric protection [ 9 ]. This consists of heating the probe surface by circulating an electric current through a resistive element.…”

Section: Introductionmentioning

confidence: 99%

Development of an Analytic Convection Model for a Heated Multi-Hole Probe for Aircraft Applications

Muro

Heckmeier

Jenkins³

et al. 2021

Sensors

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Ice accretion or icing is a well-known phenomenon that entails a risk for the correct functioning of an aircraft. One of the areas more vulnerable to icing is the air data measuring system. This paper studies the icing protection offered by a heating system installed inside a multi-hole probe. The problem is initially solved analytically, creating a tool that can be used in order to predict the heating performance depending on the flying conditions. Later, the performance of the real system is investigated with a heated five-hole probe prototype in a wind tunnel experiment. The measured results are compared with the predictions made by the analytical model. Last, the icing protection provided by the system is estimated with respect to flying altitude and speed. As a result, a prediction tool that can be used in order to make quick icing risk predictions for straight cylindrical probes is delivered. Furthermore, the study provides some understanding about how parameters like altitude and air speed affect the occurrence of ice accretion.

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Numerical Simulations and Sensitivity Analysis of Ice Formation on Fan Blades

Müller,

Flassig,

Flassig

2024

Journal of Turbomachinery

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In-flight icing, the formation of ice during flight, poses risks to the safety and reliability of aircraft. Due to environmental conditions, ice accumulation occurs on the low-pressure compressor blades of an engine, diminishing aerodynamic performance and potentially causing damage to the engine. Numerical simulations of ice accretion are conducted on the blades of the NASA Rotor 67 utilizing the Computational Fluid Dynamics (CFD) software ANSYS CFX and the in-flight icing software FENSAP-ICE. One-dimensional and two-dimensional sensitivity studies aim to analyze the influences of temperature, droplet diameter and liquid water content (LWC) on the resulting ice build-up on the blade. The analyses reveal that ice accumulates predominantly at the leading edge of the blade, where collection efficiency is maximal. Additionally, an ice layer forms at the blade root on the pressure side. While LWC and temperature exerts a significant influence on the ice mass, only a marginal impact on droplet diameter is observed.

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In-flight Icing: Modeling, Prediction, and Uncertainty

Cited by 3 publications

References 73 publications

Numerical Simulation of an Electrothermal Ice Protection System in Anti-Icing and Deicing Mode

Numerical Simulation of an Electrothermal Ice Protection System in Anti-Icing and Deicing Mode

Development of an Analytic Convection Model for a Heated Multi-Hole Probe for Aircraft Applications

Numerical Simulations and Sensitivity Analysis of Ice Formation on Fan Blades

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