Aircraft leading edges are commonly protected from potentially hazardous ice build-up by means of thermal anti-icing systems. Investigations have been carried out into the heat transfer characteristics of a typical aero-engine intake fitted with a jet impingement hot air anti-icing system to improve modelling techniques and thus facilitate optimisation of this type of system. The results of experimental investigations into the internal lipskin heat transfer characteristics, a re-assessment of external heat transfer, conduction effects and a simple freezing option for areas of lipskin falling below zero degrees centigrade have been used to refine a computer thermal model. Proposed changes to modelling techniques are validated by reference to temperatures recorded during flight testing in dry air and in natural and simulated icing conditions. The resultant prediction capability in terms of skin temperature levels and residual ice quantities is satisfactory.
Heat transfer characteristics of an aero-engine intake fitted with a hot air jet impingement anti-icing system
Waermeuebergangseigenschaften eines Flugzeugtriebwerkseinlaufs mit einem Enteisungssystem
ASME Proc. of the 1988 Nat. Heat Transfer Conf. ; HTD-96 , Jul ; 163-170
1988
8 Seiten, 6 Bilder, 1 Tabelle, 12 Quellen
Conference paper
English
Thermal Modeling of a Rotating Heat Pipe Aero-Engine Nose Cone Anti-Icing System
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