Rohr, Inc.

Christian Soria

Charles Michael Biset

Michael John Layland

Song Chiou

Jose S Alonso-Miralles

Claude Marc Hubert

Andrew S Gurney

Jihad I Ramlaoui

Norman John James

Anthony Lacko

Christopher Charles Koroly

Johann Steven Schrell

Alan J Binks

Sreenivas Narayanan Nampy

Hwa-Wan Kwan

Jinqiu Jacques Lu

Brian A Sherman

Wentaur Eugene Chien

David Forsey

Kevin I Strong

Andrew Mai-Tuan Hoang

Raphael Lozano

Claude Hubert

A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.

Track beam with composite lug

A nacelle is provided that includes an outer structure and an inner structure. The inner structure includes a support structure, a first core cowl and a second core cowl. The support structure includes a plurality of first hinges, a plurality of second hinges, a plurality of longitudinal rails and a plurality of crossover rails spaced longitudinally along and connected to the longitudinal rails. Each of the first hinges is connected to a respective one of the crossover rails at a first distal end of the respective crossover rail. Each of the second hinges is connected to a respective one of the crossover rails at a second distal end of the respective crossover rail. The first core cowl is pivotally mounted to the support structure by the first hinges. The second core cowl is pivotally mounted to the support structure by the second hinges.

Support structure for inner cowls of an aircraft propulsion system

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 thrust reverser pivot door may comprise a support structure configured to pivot between a stowed position and a deployed position, and a pivot door outer skin coupled to the support structure, wherein a forward lip of the pivot door outer skin is configured to extend forward of a torque box and overlap the fan case to advantageously increase the overall size or area of the pivot door.

Thrust reverser pivot door with extended forward edge

Manufacturing processes is provided for forming a thrust reverser cascade an aircraft propulsion system. The thrust reverser cascade may include an array of vanes connected to and extending laterally between longitudinally extending first and second strongback rails. In one of the processes, the forming of the thrust reverser cascade includes additive manufacturing the first strongback rail and/or at least one of the vanes. This first strongback rail may include a length of fiber which extends more than eighty-five percent of a longitudinal length of the first strongback rail.

Additive manufacturing fiber-reinforced, thrust reverser cascade

A nacelle for an aircraft propulsion system includes a core cowl portion, a bifurcation portion and an extension portion. The core cowl portion extends about a centerline to the bifurcation portion. The bifurcation portion is connected to and extends radially between the core cowl portion and the extension portion. The extension portion projects out from the bifurcation portion and circumferentially extends over the core cowl portion. The extension portion includes an acoustic panel and a structural reinforcement. The acoustic panel includes a cellular core between a perforated face skin and a back skin, wherein the face skin is radially inboard of the back skin. The structural reinforcement is bonded to the back skin and structurally reinforces the acoustic panel.

Nacelle with bifurcation extension and integral structural reinforcement

Aspects of the disclosure are directed to a panel configured for use on an aircraft nacelle, comprising: a first skin, a second skin, a first core portion coupled to the first skin and the second skin, a second core portion coupled to the first skin and the second skin, and an insert coupled to the first skin, the second skin, the first core portion, and the second core portion, the insert forming a corner fitting between the first core portion and the second core portion.

Panel and insert for corner radii

A panel for attenuating noise includes a porous first skin, a second skin, and a core connected between the porous first skin and the second skin. The core includes a corrugated body and a stringer body. The corrugated body includes a plurality of corrugations configured from at least a plurality of baffles and a plurality of porous septums. Each of the corrugations includes a respective one of the baffles and a respective one of the porous septums. A first of the corrugations forms a first channel that extends laterally between and longitudinally along a first of the baffles and a first of the porous septums. The stringer body includes a plurality of sidewalls arranged longitudinally along the first channel. Each of the sidewalls is disposed within the first channel and configured to fluidly isolate longitudinally adjacent portions of the first channel from one another.

Acoustic panel with sidewall stringers

A panel is provided for attenuating noise. This panel includes a porous first skin, a second skin and a core, which is connected between the porous first skin and the second skin. The core includes a corrugated body and a plurality of stringer bodies. The corrugated body includes a plurality of corrugations configured from at least a plurality of baffles and a plurality of porous septums. Each of the corrugations includes a respective one of the baffles and a respective one of the porous septums. A first of the corrugations forms a first channel that extends laterally between a first of the baffles and a first of the porous septums. The stringer bodies are spaced longitudinally along the first channel. Each of the stringer bodies includes a first sidewall disposed within the first channel and configured to fluidly isolate longitudinally adjacent portions of the first channel from one another.

A nacelle may comprise a noise suppressing structure. The noise suppressing structure may comprise a plurality of noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The plurality of noise suppressing cells may contact the perforated layer of material and the non-perforated layer of material at an acute angle (e.g., between twenty and seventy-five degrees) such that the plurality of noise suppressing cells are non-orthogonal to the perforated layer of material and the non-perforated layer of material. Further, each of the plurality of noise suppressing cells may comprise a hexagonal cross-sectional profile. Further still, the noise suppressing structure may comprise a support structure comprising a plurality of support members, wherein the plurality of noise suppressing cells are situated within the support structure.

Acoustic structural panel with slanted core

Aspects of the disclosure are directed to a system configured to selectively hold open an aircraft engine cowl, comprising: a rod, a slider coupled to the rod, a track coupled to the slider, a latch coupled to the track. Aspects of the disclosure are directed to a nacelle system of an aircraft, comprising: an engine case, a bracket attached to the engine case or a cowl, a rod coupled to the bracket via a bearing, a clevis coupled to the rod, a slider coupled to the clevis, a track coupled to the slider and to the engine case or the cowl, and a latch coupled to the track that is configured to control a translation of the slider along the track based on a state of the cowl.

Track mounted hold open rod

A nacelle is disclosed. The nacelle may include an inner fixed structure ('IFS') comprising a first half, the first half comprising a central barrel portion, wherein the first half includes a first member that extends radially outward from the central barrel portion and a second member that extends radially outward from the central barrel portion radially opposite the first member, a first support structure overlaid by a first composite material that extends axially along a confluence between the central barrel portion and the first member, the first support structure configured to contact a second half comprising a second central barrel portion, and a second support structure overlaid by a second composite material that extends axially along the confluence between the central barrel and the second member, the second support structure configured to contact the second half.

Aircraft thrust reversing assembly IFS support structure

A fiber preform is provided. The fiber preform may comprise a base including a fiber weave with a plurality of fibers oriented in three directions. A plurality of legs may extend a first height from the base and include a fiber weave with the plurality of fibers oriented in three directions. A fiber reinforcement may be disposed proximate the legs with a second height equal to the first height. The fiber reinforcement may comprise a first ply and a second ply oriented orthogonal to the first ply in a plane parallel to the legs.

Composite preforms with supplemental load bearing plies

A panel for a nacelle structure that surrounds a jet engine core includes a longitudinally extending, generally semicircular center region, an upper bifurcation region, a lower bifurcation region, a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide, and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide. A bypass duct is formed in a space between the panel and the nacelle structure. A hinge beam structure and latch beam structure are integrally formed with the panel. An inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region. The outer skin layer may have an acoustic treatment, such as being perforated in at least the center region and the upper and lower bifurcation regions. In this way, a separate hinge beam and latch beam are not used, and therefore there is no need to couple the panel to the respective beams.

Growing community of inventors

La Mesa, CA, United States of America

Christian Soria