Patent ID: 9239030
Filing Date: 2016-01-19
CPC Classification: B64D,F01D,F02C,F02K,F05D

Claim Text:
1. A nacelle structure for a gas turbine engine comprising: an outer nacelle surrounding a fan section and defining an outer boundary of a bypass flow passage; an inner nacelle surrounding a core engine section and defining an inner boundary of the bypass flow passage; a panel of the inner nacelle moveable between an open position providing access to the core engine section and a closed position; a lock supported within the inner nacelle proximate the panel, the lock including an electric actuator for moving a locking pin between a locked position preventing opening of the panel and an unlocked position; a blocker mounted to a fixed structure of the core engine section blocking movement of the locking pin when the locking pin is in the locked position, wherein the locking pin is spaced radially apart from the blocker when in the locked position; and a series of latches providing a latching function for holding the panel in the closed position; wherein operation of the lock is independent of the latching function.