Multi-physics Simulation of Aircraft Ice Protection System and Ice Impact with Turbofan Blades

Baruzzi, Guido S.; Oswald, Marco; Pett, Alexander; Gerber, Bence; Rajarao, PL; Sasanapuri, Balasubramanyam; Harwood, R. S.

doi:10.2514/6.2016-4353

Cited by 4 publications

(2 citation statements)

References 4 publications

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“…The commercial software FENSAP-ICE and CANICE, which are specifically used for anti-icing calculations, have been developed abroad through a lot of research work carried out in the field of numerical simulation studies. For instance, Baruzzi et al [5] simulated the ice accretion on the engine nacelle by using Fluent and FENSAP-ICE and then used ANSYS AUTODYN to simulate the impact of ice accumulation on the blades after activating the anti-icing system. Jung et al [6] constructed a metamodel by using neural networks to evaluate the performance of the electric heating anti-icing system for a rotorcraft engine intake and validated the metamodel based on the performance of the electric heating anti-icing system.…”

Section: Introductionmentioning

confidence: 99%

Super-cooled droplet impact and ice accretion on an aircraft engine nacelle lip

Wang,

Guan,

et al. 2024

J. Phys.: Conf. Ser.

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This manuscript concentrated on the icing phenomenon on the lips of an engine nacelle. Numerical simulation was employed to establish the airflow, supercooled droplet impact, and engine nacelle ice accretion models. The study investigated the airflow field near the lip, the characteristics of supercooled droplet impact, and the ice accretion near the lip under different flight conditions. The computational results indicated that due to the effects of nozzle contraction and flow extraction, a low-pressure, high-velocity, and low-temperature region appeared on the inner side of the lip, leading to ice accretion on the nearby wall. The maximum collection efficiency on the lip surface at 20, 000 ft was slightly higher than that at 10, 000 ft, with a maximum value of approximately 0.6. In the computed conditions of this study, as the flight altitude and Mach number increased, the ice thickness on the lip surface increased and the ice spread inward, posing a significant risk of ingestion after detachment.

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Section: Introductionmentioning

confidence: 99%

Super-cooled droplet impact and ice accretion on an aircraft engine nacelle lip

Wang,

Guan,

et al. 2024

J. Phys.: Conf. Ser.

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“…Piccolo Tube Anti-Icing (PTAI) is the most efficient and reliable method for preventing ice accumulation on aviation critical surfaces [3], but non-uniform heat transfer occurs on nacelle lip-skins, since hotspots and cold-spots have the maximum heat transfer rate and the minimum heat transfer rates on nacelle lip-skin, respectively. As a consequence, ice accumulates downstream from the nacelle lip-skin area.…”

Section: Introductionmentioning

confidence: 99%

Effect of nozzle rotation angles and sizes on thermal characteristic of swirl anti-icing

Ismail

Wang

2018

J Mech Sci Technol

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The Federal Aviation Administration requires all aircraft manufacturers to adhere to maximum noise level standards. Thus, a Bias Acoustic Liner is introduced, to intensify the noise equipment system, as well as prevent ice accumulation on the nacelle D-chamber. The hotspot phenomenon, by the Piccolo Tube Anti-Icing system, could damage the Bias Acoustic Liner. Therefore, a Swirl Anti-Icing system is further investigated, to reduce the hotspot effect on the Bias Acoustic Liner. The present work investigates the effect of nozzle rotation angles at various mass-flow-rates of hot-air supplied on the nacelle lip-skin temperature distribution, in order to enhance the Swirl Anti-Icing system's performance. The effect of the nozzle ratio area on the swirl anti-icing system's performance to be discussed in the present work. The simulation results show that the hotspot temperature decreases by 26% and the cold spot temperature increases by 18%, as the nozzle to be rotated from 0 o to 13 o towards the inner skin. However, the nozzle ratio area shows a negative effect on the swirl anti-icing performance, where the hotspot temperature increases by 6.7% and the cold spot temperature decreases by 30.2% with the ratio nozzle area increasing from 0.1083 to 0.8354. According to Swirl Anti-Icing empirical values, the average Nusselt number is directly proportional to the average Reynolds number. In conclusion, the temperature distribution on the nacelle lip-skin and the Swirl Anti-Icing system's performance improves as the angle of nozzle direction increases, rotating towards the inner skin. Swirl Anti-Icing does not generate hotspot on the inner skin, thus making it suitable for use in a Bias Acoustic Liner system.

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Effects of Film Holes Position on Anti-icing Characteristics of Aero-engine Inlet Adjustable Blade

Jiang,

Gong,

et al. 2023

Lecture Notes in Mechanical Engineering

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Multi-physics Simulation of Aircraft Ice Protection System and Ice Impact with Turbofan Blades

Cited by 4 publications

References 4 publications

Super-cooled droplet impact and ice accretion on an aircraft engine nacelle lip

Super-cooled droplet impact and ice accretion on an aircraft engine nacelle lip

Effect of nozzle rotation angles and sizes on thermal characteristic of swirl anti-icing

Effects of Film Holes Position on Anti-icing Characteristics of Aero-engine Inlet Adjustable Blade

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