[논문]대기 결빙 조건에서의 전기열 방식 결빙보호 시스템에 관한 전산해석

프린스 라즈; 명노신

doi:10.6112/kscfe.2016.21.1.001

대기 결빙 조건에서의 전기열 방식 결빙보호 시스템에 관한 전산해석
COMPUTATIONAL ANALYSIS OF AN ELECTRO-THERMAL ICE PROTECTION SYSTEM IN ATMOSPHERIC ICING CONDITIONS 원문보기

한국전산유체공학회지 = Journal of computational fluids engineering, v.21 no.1 = no.72, 2016년, pp.1 - 9

프린스 라즈 (경상대학교 대학원 기계항공공학부) , 명노신 (경상대학교 대학원 기계항공공학부)

Abstract ▼ AI-Helper

Atmospheric icing may have significant effects not only on safety of aircraft in air, but also on performance of wind turbine and power networks on ground. Thus, ice protection measure should be developed to protect these systems from icing hazards. A very efficient method is the electro-thermal de-icing based on a process by which ice accretion is melted and blown away through aerodynamic forces. In this computational study, a state-of-the-art icing code, FENSAP-ICE, was used for the analysis of electro thermal de-icing system. Computational results including detailed conjugate heat transfer analysis were then validated with experimental data. Further, the computational model was applied to the DU21 airfoil section of NREL 5MW wind turbine with calculated heater parameters.

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가설 설정

The ice accretion results at various time steps with IPS are also shown in Fig. 10. Shedding of ice and dramatic reduction of ice accretion can be easily observed.
The maximum solid surface temperature on the airfoil is shown in Fig. 9. The trend shown in the DU21 surface temperature remains the same as NACA0012 surface temperature. The maximum temperature on the surface of airfoil does not exceed very much above 288 K.

제안 방법

In order to validate the computational model, an electro-thermal ice protection system installed at the leading edge of NACA 0012 airfoil was analyzed. It turned out that the present computational results, in particular, conjugate heat transfer predictions compare reasonably with experimental data in most cases.
In this study, performance of an electro-thermal ice protection system of aircraft and wind turbines in atmospheric icing conditions was investigated. The computational methods based on partial differential equations were used for the analysis of air flow, droplet impingement, ice accretion, conjugate heat transfer, and thermal ice protection systems.

대상 데이터

8288 m[22]. The model was fabricated into two pieces: a leading edge section(0.224 m) of chord, and a wooden after-body(0.6604 m). The leading edge material composition and thickness information are given in Fig.
In this study, the analysis of electro-thermal ice protection system is conducted for NACA0012 airfoil using a state-of-the-art CFD code to validate the current computational model. The validated computational model is applied to a wind turbine blade section DU21.
The wind turbine blade selected for current analysis is DU21 and it is one of the airfoil sections of NREL 5MW wind turbine[20,21]. The target temperature is assumed to be 288 K and all heater parameters are described in Table 1.

이론/모형

Accurate air-flow solution around the NACA0012 airfoil is predicted by the finite volume Navier-Stokes-Fourier code. The collection efficiency results are shown in Fig.
The challenge is to minimize power consumption while avoiding ridges on the upper surface of the wing and wind turbine blades. In this study, the analysis of electro-thermal ice protection system is conducted for NACA0012 airfoil using a state-of-the-art CFD code to validate the current computational model. The validated computational model is applied to a wind turbine blade section DU21.
The target temperature is assumed to be 288 K and all heater parameters are described in Table 1. The calculated heater geometrical parameters(heater length and area) are used to model the heater and the calculated heater power requirement is used in FENSAP for the current computational model.
The compressible Navier-Stokes-Fourier code based on the finite volume method and the Roe's approximate Riemann solver, FLUENT, are used.
The droplet impingement solver DROP3D is based on the finite element method and the Newton’s method is used to linearize the non-linear governing equations.

참고문헌 (22)

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상세보기
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상세보기
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상세보기
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상세보기
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원문보기 상세보기
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상세보기
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상세보기
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상세보기
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상세보기
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상세보기
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상세보기
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