Investigation of Coupled Heat Transfer and Electrothermal De-icing System of Helicopter Blade

DOI

10.2991/lemcs-14.2014.144How to use a DOI?

Keywords

helicopter blade; numberical simulation;de-icing; runback ice; surface temperature

Abstract

Numerical simulation of helicopter blade de-icing procession in typical conditions in two-dimensional was expanded. The Finite Volume Method was used to discretize the governing equations. The temperature distribution of the de-icing system was obtained by solving the coupled equations of external icing, internal heat conduction and the mixed ice-water phase transfer. The whole calculation process was based on Messinger model and the improved enthalpy method. Two observation points were placed at the stagnation point in the leading-edge area and out of the runback area on the lower surface to detect the ice thickness in these areas in order to evaluate the effect of the structure designed. The effects of different icing conditions on the temperature distribution of the de-icing system were analyzed. Further, taking into account of the deficiencies of the limited heat protected range and runback ice of the aimed simulation system, configuration development and numerical simulation on the heat protected range, the places of heating wires and the heat power distribution were presented.

Copyright

© 2014, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

Download article (PDF)

TY  - CONF
AU  - Bo Yang
AU  - Shinan Chang
AU  - Jianping Fu
AU  - Lin Cheng
PY  - 2014/05
DA  - 2014/05
TI  - Investigation of Coupled Heat Transfer and Electrothermal De-icing System of Helicopter Blade
BT  - Proceedings of the International Conference on Logistics, Engineering, Management and Computer Science
PB  - Atlantis Press
SP  - 630
EP  - 635
SN  - 1951-6851
UR  - https://doi.org/10.2991/lemcs-14.2014.144
DO  - 10.2991/lemcs-14.2014.144
ID  - Yang2014/05
ER  -