The Boeing Company

Zachariah B VanDeMark

Chen Chuck

Tunde Abiodun Olaniyan

David John Barene

Naimishkumar Harpal

Everette Desmond Gray

Leonard J Hebert

Michael L Sangwin

Garry Anthony Booker

Stephen Richard Dark

Daniel Paul Brzozowski

Nathan Owen Packard

Minkoo Han

Hin-Fan M Lau

Frederick W Roos

Douglas G Cogswell

A system may include a first duct including an air inlet end and an air outlet end, and a valve within the first duct and configured to open to allow or close to prevent fan duct air from the air inlet end to pass through to the air outlet end of the first duct. The system may also include a second duct including a first end and a second end. The first end of the second duct may be coupled to a sidewall of the first duct and configured to allow the fan duct air to flow from the first duct to the second duct. The system may also include a resonance chamber coupled to the second end of the second duct and configured to allow the air in the resonance chamber to act as a spring causing the air in the second duct to oscillate at a predefined frequency.

Ducted inlet for reducing flow oscillations

Compression mold assembly for forming a preform of a cascade includes first and second die elements and an axis of alignment. Line of removal of a formed preform is positioned perpendicular to a plane perpendicular to the axis of alignment. First die portion includes first curved surface forming interior surface of first strong back and second die portion includes first curved surface forming interior surface of a second strong back of a cell of a formed preform. Second die portion includes second curved surface forming an interior surface of a first vane on forward side of the cell of the formed preform and first die portion further includes first wall member which extends along line of removal and a second wall member which extends angularly from first wall portion forming an interior surface of a second vane positioned on an aft side of the cell.

Compression molded cascades with two piece mold

A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.

Method for manufacturing and assembly of a thrust reverser cascade

A liner assembly includes a core and a septum coupled to the core. The liner assembly also includes a facesheet coupled to the septum. The facesheet includes a plurality of slots defined therethrough. Each slot of the plurality of slots is substantially continuous over a selected portion of a surface and perpendicular to or parallel to a centerline of the liner assembly.

Liner assembly, engine housing, and methods of assembling the same

A mold insert assembly includes a base section having a base side removably attachable to a base plate of a mold and a first interface surface having a notched portion thereon. A first section includes a first interface side with a first interconnecting tab sized to engage the notched portion of the base section when the first interface side abuts the first interface surface, the first section further including an adjoining side having an interconnecting notch. A second section includes a second interface side having a second interconnecting tab, where the second interconnecting tab is sized to engage the interconnecting notch of the first section when the second interface side abuts the adjoining side, and where the base section, the first section, and the second section when assembled form a contoured insert configured to create a contoured cavity in a part formed within the mold.

Mold insert assembly

Systems and methods are provided for a thrust reverser system with a straight vane thrust reverser cascade. The thrust reverser system may also include a blocker door and a turning door. The blocker door may divert air flowing within a bypass flow path of the aircraft propulsor to flow through the thrust reverser cascade. The turning door may then deflect air flowing from the thrust reverser cascade to provide reverse thrust. The straight vane thrust reverser cascade may allow for increased reverse thrust and/or a smaller, more efficient, aircraft propulsor.

Dual turn thrust reverser cascade systems and methods

There is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly has inflatable cascade members for inflation with a pressurized fluid. The inflatable cascade members are movable between a stowed deflated state and a deployed inflated state. Each inflatable cascade member has a forward end, an aft end, and a body. The body has circumferential vanes each having a first non-inflatable rigid side attached adjacent to a second inflatable flexible side. The body further has inflatable support members that are spaced apart and longitudinally extending, and coupled in a perpendicular arrangement to the circumferential vanes. The body further has a plurality of flow openings defined between the circumferential vanes and the inflatable support members. Each inflatable cascade member further has first and second extendable side supports coupled to respective first and second side ends of the body.

Inflatable cascade assembly, system, and method for a cascade thrust reverser system

Thrust-reverser assemblies that utilize active flow-control and systems and methods including the same are disclosed herein. The thrust-reverser assemblies define a forward-thrust configuration and a reverse-thrust configuration. The thrust-reverser assemblies include a bullnose fairing that defines a portion of a reverser duct and an active flow-control device. The active flow-control device is located to energize a boundary layer fluid flow within a boundary layer that is adjacent to the bullnose fairing to resist separation of the boundary layer from the bullnose fairing when the thrust-reverser assembly is in the reverse-thrust configuration. The methods include flowing a thrust-reverser fluid stream through the reverser duct to generate the boundary layer and energizing a boundary layer fluid flow within the boundary layer with an active flow-control device to resist separation of the boundary layer from the bullnose fairing.

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Snohomish, WA, United States of America

Zachariah B VanDeMark