Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

Wei, Dong; Zhu, Jianjun; Zheng, Mingming; Chen, Y.

doi:10.2514/1.b35378

Cited by 40 publications

(21 citation statements)

References 42 publications

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“…[1][2][3][4][5] The current anti-/de-icing methods fall into two distinct categories: (1) anti-icing (i.e., ice prevention) and (2) deicing (i.e., ice removal). The methods can also be classified into three categories: 6,7 (1) the liquid-based, such as weeping wings, (2) the mechanical-based, such as pneumatic boots, and (3) thermal-based, such as hot-air 8 and electro-thermal systems. 6 The breakthrough of the significant technology in the area of aerodynamics, materials, and power raised many challenges on the current anti/de-icing methods.…”

Section: Introductionmentioning

confidence: 99%

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Meng

et al. 2019

Physics of Fluids

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Anti-icing performance using the surface dielectric barrier discharge plasma actuator is studied using detailed visualization and surface thermal measurements. To reveal the physical mechanism of coupled aerodynamic and thermal effects on anti-icing, three types of actuators are designed and mounted on a NACA 0012 airfoil. The coupled aerodynamic and thermal effects are confirmed in still air. The results show that the plasma actuation is effective for in-flight anti-icing, and the anti-icing performance is directly related to the design of the plasma actuators based on the coupled aerodynamic and thermal effects. When the direction of plasma induced flow is consistent with the incoming flow, the heat generated by plasma discharge is concentrated in the region of the actuator and the ability of the actuator for heat transfer downstream is relatively weak during the anti-icing. When the induced flow is opposite to the incoming flow, there is less heat accumulation in the actuator region, while the ability of heat transfer downstream becomes stronger. With the consistent and opposite direction of induced flow, the plasma actuation can ensure that 57% and 81% chord of the lower surface of the airfoil are free of the ice accumulation, respectively. Another actuator is designed to induce the air jets approximately perpendicular to the airfoil surface. This exhibits both a stronger ability of heat accumulation locally and heat transfer downstream and hence ensures that there is no ice on the entire lower surface of the airfoil.

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Section: Introductionmentioning

confidence: 99%

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Meng

et al. 2019

Physics of Fluids

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“…7 The law of ideal gas Eq (1) relates density to temperature and pressure. A linearized equations system was constructed and solved from Eq (2) and (3).…”

Section: Mathematical Modelmentioning

confidence: 99%

“…1 In recent years, the practical concept of icing and anti-icing, such as the impingement of supercooled large droplets (SLD), the flow and heat transfer of runback water in glazing or mixing icing, and the effect of roughness on ice accretion have all been gradually developed to enhance icing detection or anti-icing system design. 2 If moisture affects an aircraft's forward facing surfaces and these surfaces are at or below 0°C, an ice build-up may seriously change the aerodynamic characteristics. This refers in particular to tiny objects with greater catch rate effectiveness than large ones, since tiny quantities of ice will generate relatively larger shape changes, posing a significant performance and safety risk.…”

Section: Introductionmentioning

confidence: 99%

Untitled

2020

IRATJ

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There has always been an ongoing effort to improve aircraft anti-icing systems. Aircraft Icing poses a dangerous to the performance and safety, so it has a great concern for the airplane manufacturing and Airliners. The geometry of anti-icing system consists of a piccolo tube inside a swept wing with three rows of round jets based on NACA 23012 air foil. Commercial ANSYS CFD software is used to solve a compressible internal airflow, an external cold airflow and the thermal conduction in the solid skin. By modelling only the effects of conductive, viscous and convective heat transfer in a dry atmosphere the complexity of this procedure conjugate heat transfer is reduced. Used three dimensional Navier-Stokes computer code to simulate the jet flow impinging with circular configuration and heat transfer. The flow field of all turbulent regions was modelled by using the twoequation k ω Shear Stress Transport (SST) turbulence model. This research work indicates a strong potential of using CFD in dynamic of partial wing segment including thermal anti-icing system model at different external flow parameters development and validation.

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“…It correlates the mass transfer and heat transfer processes in order to calculate the accreted ice height and predict ice shape. Dong and Zhu et al [12,13] conducted both numerical and experimental studies to evaluate a newly-developed hot-air anti-icing system applied to a full-scale nonrotating cone model. The surface temperature distribution under different icing conditions were measured by thermocouples and simulated by a conjugate heat transfer computation.…”

Section: Introductionmentioning

confidence: 99%

An Experimental Investigation on the Unsteady Heat Transfer Process over Ice Accreting Surfaces of Aero-engine Spinner Models

2017

9th AIAA Atmospheric and Space Environments Conference

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The heat transfer process in an aero-engine icing event is highly dependent on the oncoming flow conditions and local impingement status. In the present study, an experimental study was conducted to investigate the transient heat transfer during the ice accretion process over three typical types of rotating aero-engine spinners (i.e., conical, coniptical, and elliptical). The experiment study was performed in the Iowa State University Icing Research Tunnel (ISU-IRT) with a scaled aero-engine fan model operated under various icing conditions. The details in the unsteady heat transfer process were resolved using an infrared thermal imaging system. The time-evolutions of the surface temperature at different monitoring points were recorded and illustrated. Based on a simplified heat balance model, the dynamic processes of the latent heat release during liquid-solid phase change and its competing effects with convective/conductive heat transfer were evaluated in accordance with the surface temperature variation. The experiments demonstrated the effects of the spinner profiles on the unsteady local heat transfer process. It was found that the conical-shaped spinner would have more uniform ice accretion as indicated by the equivalent temperature distribution, while the coniptical and elliptical spinners displayed obvious temperature gradient along the surface during the icing processes. The dynamic heat transfer stages of the different icing processes (i.e., glaze and rime) are also elucidated in details.

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Thermal Analysis and Testing of Nonrotating Cone with Hot-Air Anti-Icing System

Cited by 40 publications

References 42 publications

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Untitled

An Experimental Investigation on the Unsteady Heat Transfer Process over Ice Accreting Surfaces of Aero-engine Spinner Models

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