Patent ID: 8899013
Filing Date: 2014-12-02
Classification: F01D,F02K,F05D,Y02T

Abstract:
1. A thrust reverser for a turbojet engine nacelle comprising: at least one fixed front frame mounted downstream of a fan case of a turbojet engine and directly or indirectly supporting at least one flow deviating means; an outer cowl translatably mounted along a longitudinal axis of the turbojet engine nacelle, wherein the flow deviating means and the front frame comprise complementary locking/unlocking means configured to engage the flow deviating means with the front frame in a reverse jet situation and to detach the flow deviating means from the front frame during a maintenance operation of said thrust reverser, wherein said outer cowl is configured to translate the flow deviating means during the maintenance operation once the flow deviating means are detached.