Rohr, Inc.

Johann Steven Schrell

Thomas Paolini

Pablo T Sanz Martinez

Brian A Sherman

Guinevere Berg

Samantha Landis

Andrew Cai

Jihad I Ramlaoui

Christian Soria

Andrew J Strutt

Raphael Lozano

Kevin I Strong

Andrew Mai-Tuan Hoang

An air inlet for an aircraft propulsion system nacelle includes an outer skin, an inner skin, a lip skin, and a forward bulkhead. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The forward bulkhead includes a first bulkhead portion and a second bulkhead portion. The first bulkhead portion and the second bulkhead portion are mounted to the outer skin. The first bulkhead portion and the second bulkhead portion are mounted to the inner skin. The first bulkhead portion includes a rigid body material and the second bulkhead portion includes a flexible body material.

Air inlet bulkhead assembly for an aircraft propulsion system

A chevron ring is disclosed. In various embodiments, the chevron ring includes an attachment ring; and a chevron, the chevron connected to and extending downstream of the attachment ring and having a trailing edge portion, the chevron defining a hollow portion between the attachment ring and the trailing edge portion.

Gas turbine engine exhaust chevrons

A component is provided that includes a monolithic structure and a fitting element. The monolithic structure includes first and second outer panels, and spars disposed between the first and second outer panels. The width of the monolithic structure extends between a fitting end and a distal end. The spars extend widthwise between the first and second outer panels. The spar fitting end of each spar has a Y-shaped configuration with first and second finger walls, and a channel disposed there between. Both the first and second finger walls have a divergent end and a distal end. The channel has a closed end and an open end defined at the finger wall distal ends. The fitting element has a body with one or more blades extending outwardly therefrom. Each blade is received in and mates with a spar fitting end channel and is bonded to the spar fitting end.

Component with monolithic structure having blind interface joint

An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.

Mixed flow exhaust thrust reverser with area control nozzle systems and methods

A method for forming a fiber-reinforced thermoplastic control surface includes forming first and second skins from a fiber-reinforced thermoplastic resin. The method further includes overmolding fiber-reinforced thermoplastic features onto the first skin and/or second skin, including stiffener structures, sidewalls, and/or hinges. The method further comprises welding or consolidating the first and second skins together, along with the associated internal features overmolded thereon to form a single-piece, stiffened, fiber-reinforced thermoplastic control surface.

Thermoplastic composite panel systems and methods

A panel for an active laminar flow control arrangement may comprise a longitudinal wall and one or more division walls extending from the longitudinal wall and extending between the first end and the second end. The panel may be coupled to a nacelle outer skin via a plurality of adhesive fasteners pre-installed onto an inner surface of the outer skin and onto stiffeners and/or stringers associated with the outer skin.

Active laminar flow control plenum panel arrangements and installation methods

An assembly is provided for active laminar flow control. This assembly includes a panel, which panel includes an outer skin, an inner skin and a plurality of plenums between the outer skin and the inner skin. Each of the plurality of plenums is fluidly coupled with a respective array of perforations through the outer skin. The panel is constructed from fiber-reinforced composite material.

Active laminar flow control system with composite panel

An active laminar flow control arrangement may comprise an outer skin having an inner surface, an outer surface, and a perforated area, and a panel coupled to the inner surface. The panel may comprise a longitudinal wall, a sidewall extending from the longitudinal wall, a ridge intersecting the sidewall, a cavity disposed in the panel and at least partially defined by the sidewall and the longitudinal wall, and a division wall disposed in the cavity and extending from the longitudinal wall, wherein the division wall divides the cavity into a first plenum and a second plenum. The longitudinal wall, the sidewall, the ridge, and the division wall may comprise a single, monolithic piece.

Active laminar flow control plenum panel arrangement

An active laminar flow control arrangement may comprise a modular arrangement comprising a plurality of frames and cover panels coupled to an outer skin having a plurality of hat stiffeners and stringers. A first cover panel may be coupled between a first frame and a first hat stiffener. A second cover panel may be coupled between a second frame and a second hat stiffener. A third cover panel may be coupled between the first cover panel and the second cover panel. The cover panels may enclose associated plenums whereby a flow of air is pumped into the arrangement for maintaining a laminar flow across an aerodynamic surface of the outer skin.

Active laminar flow control structural plenums fastened

An energy absorbing arrangement may comprise an inner barrel comprising a centerline axis, an outer barrel, a webbing extending between the outer barrel and the inner barrel and configured to be offset from a nose lip by a distance, the webbing being folded together to form a plurality of folds, the plurality of folds being stitched together via a plurality of stitches, wherein the webbing is configured to absorb energy from an object in response to the object passing through the nose lip and applying a force to the webbing.

Bird-strike energy absorbing net

A nacelle is provided for an aircraft propulsion system. This nacelle includes a stationary support, a fanlet, a thrust reverser sleeve and an interface assembly providing an interface between the stationary support, the fanlet and the thrust reverser sleeve where the fanlet and the thrust reverser sleeve are respectively in stowed positions. The stationary support extends circumferentially about an axial centerline. The fanlet includes an inlet structure and a fan cowl. The fanlet is configured to translate axially along the centerline. The thrust reverser sleeve is configured to translate axially along the centerline. The interface assembly includes a pair of interlocking components, wherein a first of the interlocking components is mounted to the fanlet at the aft end of the fanlet.

Controlling a relative position at an interface between translating structures of an aircraft nacelle

Aspects of the disclosure are directed to a system associated with a thrust reverser of an aircraft, comprising: a set of cascades incorporating a track, the track including a first track end and a second track end, a blocker door, and a link including a first link end coupled to the track and a second link end coupled to the blocker door, where the cascades are configured to translate between a stowed position and a deployed position to cause the first link end to traverse the track.

Translating cascade thrust reverser with control of blocker door

An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser cascade, a fan ramp fairing and a blocker door. The thrust reverser cascade extends along an axial centerline from a forward cascade end to an aft cascade end. The fan ramp fairing is disposed at the forward cascade end. The fan ramp fairing is configured with a fairing surface that provides a forward boundary for bypass air flowing into the thrust reverser cascade during a first mode of operation. The blocker door is configured to completely axially overlap the fairing surface during a second mode of operation.

Growing community of inventors

San Diego, CA, United States of America

Johann Steven Schrell