Rohr, Inc.

Goodrich Corporation

Rohr Industries, Inc.

Michael John Layland

Claude Marc Hubert

Norman John James

Song Chiou

Keith Towers Brown

Alan J Binks

Jia Yu

Michael R Aten

Christian Soria

Ron Long

Lee A Tichenor

Hwa-Wan Kwan

Daniel M Amkraut

Galdemir Cezar Botura

Charles Michael Biset

Daniel Paul Christy

Timothy Olson

Joseph Christopher Zecca

James Michael Roman

Brian Burkett

David Forsey

Claude Hubert

Brian Bobby Burkett

Timothy Robert Olson

Michael Ray Aten

Claude M Hubert

Chiou Song

Yu Jia

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

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.

Thrust reverser-integrated track beam and inner fixed structure

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

Translating variable area fan nozzle providing an upstream bypass flow exit

A multi-segment tool and tooling system for vacuum forming a composite part. A tool can include a first tool having first and second surfaces. A second tool can have an opening positioned on a first tool in a location other than the first surface or the second surface. The first tool and second tool can receive at least a portion of a preform composite. The first tool can have a vacuum barrier attached to the first surface and to the second surface encapsulating the preform composite and the second tool. A tooling system can include a first tool having a core and a base with a core extending upwards from the base. A second tool can be positioned upon the core where the core extends above the second tool. A vacuum barrier sealed to the base and the core can include a composite, the first tool and the second tool.

Multi-segment tool and method for composite formation

A hybrid beam for support of a nacelle panel of a jet engine is disclosed. The beam is comprised of a first longitudinal composite panel and a second longitudinal composite panel, wherein the first longitudinal composite panel is integrally affixed to the second longitudinal composite panel along a longitudinal edge. The composite panels form a composite beam structure that is substantially open with a cross-section that is generally 'L-shaped'. A plurality of hinge stations are affixed to a first side of the first longitudinal composite panel and at least one track guide is disposed on a second side of the first longitudinal composite panel. The track guides receive a head portion of a slider that is fixed to the translating jet engine nacelle panel. Each hinge station further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam.

Hybrid hinge and latch beam

A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.

Variable area fan nozzle with one or more integrated blocker doors

A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.

Inlet section of an aircraft engine nacelle

A nacelle is configured to be coupled to an underside of a wing so as to form a clearance space therebetween. The nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The first cowling can also include a flattened surface.

Nacelle

An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.

Reinforcement members for aircraft propulsion system components configured to address delamination of the inner fixed structure

A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.

Linear acoustic liner

Growing community of inventors

Bonita, CA, United States of America

Michael John Layland