Explosive decoupling system for a turbojet nozzle

Details Explosive decoupling system for a turbojet nozzle Explosive decoupling system for a turbojet nozzle

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/36 (2006.01) F01D 21/04 (2006.01) F01D 25/04 (2006.01) F01D 25/16 (2006.01) F01D 25/28 (2006.01) F02K 3/00 (2006.01) F16P 5/00 (2006.01)

Patent

CA 2444979

A system for decoupling a fan of a turbojet, the turbojet including a moving fan shaft (4) mounted on bearings (6, 8) each connected to a stationary structure (28) of the turbojet by bearing supports (26, 30), the bearing supports being fixed to the stationary structure of the turbojet via mechanical links (32, 34) serving, during normal operation of the turbojet, to transmit the forces generated by rotation of the fan, the mechanical links include explosive charges enabling the links to be broken, the explosive charges being controlled by a full authority digital engine control computer (40) on the basis of means (44) for measuring the mechanical stresses in the turbojet and of a computer model (46) simulating the static, dynamic, and thermodynamic behavior of the turbojet.

Système de découplage d'une soufflante d'un turboréacteur comprenant un arbre mobile (4) monté sur des paliers (6, 8) reliés chacun à une structure fixe (28) du turboréacteur par des supports de paliers (26, 30), les supports de palier étant fixés à la structure fixe par des liaisons mécanique (32, 34) assurant le passage des efforts engendrés par la rotation de la soufflante lors du fonctionnement normal du turboréacteur, ces liaisons mécaniques comportant des charges explosives permettant de provoquer une rupture des liaisons, les charges explosives permettant de commandées par un calculateur électronique pleine autorité (40) à partir de moyens (44) de mesure de contraintes mécaniques du turboréacteur et d'un modèle de calculs (46) simulant le comportement statique, dynamique et thermodynamique du turboréacteur.

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