Rohr, Inc.

Jinqiu Jacques Lu

Vijay V Pujar

Christian Soria

Richard Scott Alloway

Adam G Saunders

Gary Euan Bowman

Travis Michael Frazier

Frank Zabatta

Karina Alejandra Hernandez

Scott L Marshall

Gary E Bowman

A compression rod engagement apparatus is provided that includes an engagement feature, an engagement feature pin, and a mounting member. The engagement feature is attached to the engagement feature pin. The engagement feature pin is engaged with the mounting member in a home position and axial travel of the engagement feature pin along a lengthwise axis away from the home position in either axial direction is resisted by at least one spring force.

Thrust reverser compression rod engagement apparatus

A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing.

Engine exhaust skin connection system

An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.

Nacelle thrust reverser compression rod supporting system

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

A nacelle is provided for an aircraft propulsion system. This nacelle include a nacelle structure, a fanlet and an interface assembly. The fanlet is configured to translate axially along a centerline between an open position and a closed position. The interface assembly includes first and second interlocking components. One of the interlocking components is mounted to the nacelle structure, and the other one of the interlocking components is mounted to the fanlet. The first interlocking component includes a projection configured with a stop. The second interlocking component includes an aperture and a detent. The projection is adapted to extend axially into the aperture. The detent is adapted to engage the stop where the fanlet is in the closed position.

Self-locking alignment at a nacelle interface

An assembly is provided for an aircraft propulsion system. This assembly includes a fanlet and a track system configured to enable axial translation of the fanlet along a centerline between an open position and a closed position. The track system includes a first component, a second component and a lock. One of the first and the second components is configured as or otherwise includes a slider. The other one of the first and the second components is configured as or otherwise includes a track. The slider is mated with and configured to slide axially along the track. The lock is configured as or otherwise includes a bolt mounted with the first component. The lock is configured to move the bolt laterally into an aperture in the second component to prevent axial translation of the fanlet.

Lockable track system for a translating nacelle structure

A center body attachment system may comprise an engine flange, a center body mounting assembly, and a center body. The center body mounting assembly may retain the center body and the engine flange in slidable engagement, whereby the engine flange and the center body may expand and contract at different rates. The center body may comprise a housing. The housing may comprise a floating counter bore, a spring supporting the floating counter bore, and a slider radially inward of the floating counter bore and retained within the housing by a nut.

Growing community of inventors

Murrieta, GA, United States of America

Jinqiu Jacques Lu