Anti-icing apparatus and method for aero-engine nose cone

Details Anti-icing apparatus and method for aero-engine nose cone Anti-icing apparatus and method for aero-engine nose cone

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/047 (2006.01) F01D 25/02 (2006.01)

Patent

CA 2456563

An aero-engine nose cone anti-icing system using a rotating heat pipe is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source within the engine to the nose cone through a rotating heat pipe along the central shaft. A condenser and evaporator are provided which are adapted to the heat transfer requirements and space constraints in the engine.

Il s'agit d'un système de dégivrage de pointe avant de moteur d'avion au moyen d'un caloduc, pour remplacer la méthode courante qui consiste à souffler de l'air de prélèvement de compresseur chaud sur la surface de la pointe avant. La chaleur est transférée d'une source chaude à l'intérieur du moteur jusqu'à la pointe avant, au moyen d'un caloduc rotatif le long de l'arbre central. Un condenseur et un évaporateur permettent de s'adapter aux exigences de transfert thermique et aux contraintes d'espace du moteur.

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