CIRCUIT DE COMMANDE HYDRAULIQUE INTEGRE

• Main Author: JOHN HOWARD FERGUSON, JR., FRANK WOODRUFF ET JOHN R. HOFFMAN
• Format: Patent
• Language: French
• Published: 26.02.1982
• Subjects: BLASTING; COMBUSTION ENGINES; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; JET-PROPULSION PLANTS; LIGHTING; MECHANICAL ENGINEERING; WEAPONS

CIRCUIT DE COMMANDE HYDRAULIQUE INTEGRE POUR ACTIONNER LES INVERSEURS DE POUSSEE ET LA TUYERE D'EJECTION VARIABLE D'UN MOTEUR A TURBINE A GAZ D'AVION.POUR REDUIRE LE COUT ET LE POIDS, L'INVENTION INTEGRE LES DEUX CIRCUITS HYDRAULIQUES DANS UN SEUL BOITIER DE FACON QU'ILS UTILISENT EN COMMUN UN CERTAIN NOMBRE D'ELEMENTS; EN OUTRE, LE CIRCUIT DE COMMANDE DE DEPLOIEMENT ET D'ESCAMOTAGE DES INVERSEURS DE POUSSEE 4 COMPORTE UN DISTRIBUTEUR D'ORDONNANCEMENT 24 QUI EMPECHE L'APPLICATION DE L'ENERGIE HYDRAULIQUE AUX ACTIONNEURS 7 AVANT LE DEVERROUILLAGE DES INVERSEURS PAR UN ACTIONNEUR 23 DE DOIGT DE VERROUILLAGE; INVERSEMENT, LES INVERSEURS DE POUSSEE 4 DOIVENT ETRE COMPLETEMENT ESCAMOTES AVANT QUE L'ACTIONNEUR 23 DE DOIGT DE VERROUILLAGE LES VERROUILLE EN PLACE.APPLICATION AUX MOTEURS A REACTION A HAUTES PERFORMANCES. The invention is an integrated hydraulic control circuit for actuating the thrust reversers and variable exhaust nozzle on high performance gas turbine engine powered aircraft. The hydraulic circuits for both systems are integrated into a single housing and are served by common elements. The circuit for the deployment and stowage of the thrust reverser buckets is hydraulically sequenced inhibiting the application of hydraulic power to the actuators prior to withdrawal of the locking pin. In a like manner, the thrust reversers must be fully retracted before the locking pin is deployed. The hydraulic circuit for the thrust reversers also includes a pressure compensating circuit which reduces the pressure applied to thrust reverser actuators with the thrust reversers in the stowed position.