Optimization of a multi-layered heater for an electro-thermal ice protection system for a composite wing

Gallia, Mariachiara; Martuffo, Alessandro; Guardone, Alberto

doi:10.2514/6.2022-3455

Cited by 5 publications

(1 citation statement)

References 17 publications

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“…Subsequently, droplet trajectories are simulated within this flow field to determine the collection efficiency (β), using a Lagrangian approach for droplet trajectories implemented in PoliDrop [9]. Icing parameters like ice thickness and surface temperature are calculated with the in-house IPS code, PoliMIce [10,11] that also include the resolution of integral boundary layer equations to determine the convective heat transfer coefficient and the skin friction. For a detailed model description, readers are referred to the work by Arizmendi et al [10].…”

Section: Ice Protection System Simulationmentioning

confidence: 99%

Design and optimization of a modular Electro-Thermal Ice Protection System for a Horizontal Axis Wind Turbine

Gallia,

Caccia,

Guardone

2024

J. Phys.: Conf. Ser.

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In this work, an Electro-Thermal Ice Protection System (IPS) design was refined and optimized on the NREL 5 MW reference wind turbine. These improvements involved optimization of the distribution of heat flux in both the stream-wise and span-wise directions to minimize power consumption and avoid run-back ice formation. The design conditions focus on a 3-hour rime ice accretion event. The chosen optimization algorithm is a derivative-free method called Mesh Adaptive Direct Search. his optimization effort results in a 55% reduction in power consumption necessary to maintain a completely clean blade surface. The power and energy losses associated with this new optimized design are compared with those from various ice shapes and with the clean blade conditions established in the initial design phase from previous work. The new optimized design allows to keep the blade clean from ice with much larger energy saving. Indeed, only initially, during the first two hours of ice accretion, the energy losses due to this IPS design are higher than without IPS. Beyond this short initial period, substantial energy savings are achieved, especially considering that after the accretion event, the blade remains ice-free, and there are no more power losses.

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Section: Ice Protection System Simulationmentioning

confidence: 99%

Design and optimization of a modular Electro-Thermal Ice Protection System for a Horizontal Axis Wind Turbine

Gallia,

Caccia,

Guardone

2024

J. Phys.: Conf. Ser.

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Piezoelectric-Actuator De-Icing Array Design Based on Structural Vibration Modes

Miao,

Yuan,

Zhu

2024

Journal of Aircraft

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Mechanical vibration-based de-icing technology using piezoelectric actuators has demonstrated the features of low-energy consumption and nonthermal concepts in combating icing. The research on these de-icing methods presents challenges as the guidelines for piezoelectric-actuator arrangement on structures are not well established during the design stage of a de-icing system. A piezoelectric-actuator array design framework is established to give a solution for the determination of its arrangement in actual applications. The concept of placing piezo actuators according to the structural vibration modes of the substrate is first obtained by theoretical analysis. Then the influence of the dimensions and position of the piezo actuator are researched on a scale based on the half wavelength of the vibration modes. The framework for the piezo-actuator array design, based on structural vibration modes, is developed within the constraints of those parameters influencing its behavior and control of the adhesive bonding-layer thickness. The detailed piezo-actuator array is determined based on the array-design framework and is also verified by experimental measurements and de-icing tests. We further demonstrate the usefulness of the designed piezo-actuator array and the corresponding array design frameworks through the occurrence of cracks and delamination of ice on the leading-edge structure under different icing cases in an ice wind tunnel.

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UAV Icing: Aerodynamic Degradation Caused by Intercycle and Runback Ice Shapes on an RG-15 Airfoil

Wallisch,

Lindner,

Petersen

et al. 2024

Drones

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Electrothermal de-icing systems are a popular approach to protect unmanned aerial vehicles (UAVs) from the performance degradation caused by in-cloud icing. However, their power and energy requirements must be minimized to make these systems viable for small and medium-sized fixed-wing UAVs. Thermal de-icing systems allow intercycle ice accretions and can result in runback icing. Intercycle and runback ice increase the aircraft’s drag, requiring more engine thrust and energy. This study investigates the aerodynamic influence of intercycle and runback ice on a typical UAV wing. Lift and drag coefficients from a wind tunnel campaign and Ansys FENSAP-ICE simulations are compared. Intercycle ice shapes result in a drag increase of approx. 50% for a realistic cruise angle of attack. While dispersed runback ice increases the drag by 30% compared to the clean wing, a spanwise ice ridge can increase the drag by more than 170%. The results highlight that runback ice can significantly influence the drag coefficient. Therefore, it is important to design the de-icing system and its operation sequence to minimize runback ice. Understanding the need to minimize runback ice helps in designing viable de-icing systems for UAVs.

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Optimization of a multi-layered heater for an electro-thermal ice protection system for a composite wing

Cited by 5 publications

References 17 publications

Design and optimization of a modular Electro-Thermal Ice Protection System for a Horizontal Axis Wind Turbine

Design and optimization of a modular Electro-Thermal Ice Protection System for a Horizontal Axis Wind Turbine

Piezoelectric-Actuator De-Icing Array Design Based on Structural Vibration Modes

UAV Icing: Aerodynamic Degradation Caused by Intercycle and Runback Ice Shapes on an RG-15 Airfoil

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