Rohr, Inc.

Wentaur Eugene Chien

Xiaolan Hu

Julian Winkler

Landy Dong

Anthony Lacko

Christian Soria

Song Chiou

David Edward Pierick

An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array. The vanes include a first vane and a second vane. A leading edge of the first vane is disposed on the cascade inner face. A leading edge of the second vane is recessed radially into the thrust reverser cascade from the cascade inner face.

Thrust reverser cascade with offset vane leading edges

An apparatus is provided for an aircraft propulsion system. This apparatus includes a cascade structure including a thrust reverser cascade and a flow disruptor. The thrust reverser cascade extends longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between an inner face and an outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array along the inner face. The flow disruptor is arranged at the cascade inner face and forward of the vanes. The flow disruptor is configured to disrupt boundary layer air flowing towards the vanes.

Thrust reverser cascade with one or more flow disrupters

An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.

Thrust reverser cascade with one or more flow stabilizers

A nacelle inlet may comprise an aft bulkhead, an attachment ring extending in an aft direction from the aft bulkhead, an acoustic liner disposed radially inward from the attachment ring, the acoustic liner comprising a proximal skin, a distal skin, and a core disposed between the proximal skin and the distal skin, and a shroud extending longitudinally between a forward side of the shroud and an aft side of the shroud and extending circumferentially between a first end of the shroud and a second end of the shroud, wherein the shroud defines a plenum disposed between the acoustic liner and the shroud, the plenum is in fluid communication with the core via perforations in the distal skin. The plenum may serve to attenuate low frequency noise known as 'buzz saw' tones and/or alleviate pressure resonance conditions that may cause structural damage to the engine fan blades.

Inlet deep cavity flutter liner

A sound attenuation device includes an acoustic panel having a first end and a second end spaced from the first end. The first end is configured for attachment to a first mount and the second end is configured for attachment to a second mount. The acoustic panel comprises a permeable skin and a septum, the septum having a length extending between the first end and the second end.

Growing community of inventors

San Diego, CA, United States of America

Wentaur Eugene Chien