Nacelle inner flow structure leading edge latching system

• Main Authors: Cloft, Thomas G, Mercier, Claude
• Format: Patent
• Language: English
• Published: 21.08.2018
• Subjects: AEROPLANES; AIRCRAFT; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; BLASTING; COMBUSTION ENGINES; COSMONAUTICS; ENGINE PLANTS IN GENERAL; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; HEATING; HELICOPTERS; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04; JET-PROPULSION PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; PARACHUTES; PERFORMING OPERATIONS; STEAM ENGINES; TRANSPORTING; WEAPONS

A latch assembly for securing a nacelle portion of a gas turbine engine includes an engine case structure that includes a core compartment. An inner flow structure has closed and opened positions with respect to the engine case structure. The inner flow structure encloses the core compartment in the closed position and provides access to the core compartment in the opened position. A bypass flowpath is provided by a portion of the engine case structure and the inner flow structure. A seal is engaged with the engine case structure and the inner flow structure in the closed position. A latch has a latched position in which radial movement of the inner flow structure relative to the engine case structure is impeded and maintained in the closed position and an unlatched position in which the inner flow structure is permitted to move radially outward to the opened position.