Abstract: An aircraft propulsion system includes an engine assembly including a fan that moves air, and a cowl that surrounds at least a portion of the engine assembly when the cowl is in a closed position. The cowl includes an outer surface arranged away from the engine assembly that provides an aerodynamic surface. The aircraft propulsion system also includes a cowl mechanism connected to the cowl and configured to guide the cowl along a movement path from the closed position to an open position. In the open position, an entirety of the cowl is arranged farther away from a horizontal plane passing through a rotating axis of the fan than in the closed position.

Abstract: An acoustic liner is provided. The acoustic liner includes a face sheet, a back sheet spaced from the face sheet, and a core layer defining a cellular structure disposed between the face sheet and the back sheet. The core layer includes a plurality of first resonant cells coupled to the back sheet. Each of the first resonant cells includes a first cell wall coupled to the back sheet along a first cell wall base edge, the first cell wall extending from the back sheet toward the face sheet, the first cell wall further coupled to the face sheet along a first cell wall top edge, wherein the first cell wall of each of the first resonant cells comprises a surface extension that extends from a surface of the first cell wall.

Abstract: An acoustic liner may include an acoustic core having an array of resonant cells, and an acoustic screen disposed across the array of resonant cells. The resonant cells include a plurality of cell walls and a resonant space defined by the plurality of cell walls. The acoustic core may include a folded acoustic core. Additionally, or in the alternative, at least some of the resonant cells may include an oblique polyhedral cellular structure and/or a multitude of sound-attenuating protuberances. The acoustic screen may include a reticulate membrane and a support lattice.

Abstract: An apparatus and method of operating a translating cowl for a turbine engine. The translating cowl is moveable between a first position and a second position. The translating cowl includes a fixed cascade element located within and a blocker door that is operably coupled to die translating cowl. Hie blocker door is movable between a stowed position and a deployed position.

Abstract: An aircraft propulsion system includes an engine assembly including a fan that moves air, and a cowl that surrounds at least a portion of the engine assembly when the cowl is in a closed position. The cowl includes an outer surface arranged away from the engine assembly that provides an aerodynamic surface. The aircraft propulsion system also includes a cowl mechanism connected to the cowl and configured to guide the cowl along a movement path from the closed position to an open position. In the open position, an entirety of the cowl is arranged farther away from a horizontal plane passing through a rotating axis of the fan than in the closed position.

Abstract: An acoustic liner and a method of attenuating noise are provided. The acoustic liner includes a face sheet, a back sheet spaced from the face sheet, and a core layer extending between the face sheet and the back sheet. The core layer includes a plurality of resonant cells, each resonant cell including at least one cell wall coupled to the back sheet along a cell wall base edge. The at least one cell wall extends from the back sheet at an angle toward the face sheet. The at least one cell wall further coupled to the face sheet along a cell wall top edge. The resonant cell is formed in a predetermined shape and contains a volume in a space defined by the at least one cell wall, the back sheet, and the face sheet. The cell wall base edge length is greater than the cell wall top edge length.

Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and a deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.

Abstract: A latch assembly for a door is provided. The latch assembly includes a latch keep carried by one of the door and the surrounding structure and having a strike seat in which a strike may be removably received, a latch carried by the other of the door and the surrounding structure and having a catch configured to engage the strike, and a cable having a first portion secured to the other of the door and the surrounding structure and a second portion carrying the strike.

Abstract: An acoustic liner (20) with perforation (30) and method of constructing (100) an acoustic liner including forming perforations in the facing sheet by grit blasting (104) the facing sheet and mounting (106) the facing sheet to one side of a support layer having a set of partitioned cavities wherein the facing sheet closes an open face of the cavities except for the perforations to form a set of acoustic resonator cells.

Abstract: An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.

Abstract: An acoustic liner can comprise a support layer including a set of partitioned cavities defining a set of cells with open faces, as well as a first and second facing sheet operably coupled to the support layer that overlie and close the open faces. A set of aerogel fillings can be provided within at least some of the set of cells.

Abstract: A method and apparatus for a gas turbine engine including a core engine a nacelle surrounding at least a portion of the core engine and defining an interior with an opening. An access door for the opening to provide selective access to the opening where the access door provides pressure relief for the interior.

Abstract: A thrust reverser assembly for a turbine engine can include a core engine surrounded by a nacelle. A bypass duct can be formed in the space between the core engine and the nacelle. A blocker door can be movable to a deployed position extending into the bypass duct. A stop can be provided on the core engine to abut and support force applied to the deployed blocker door. The stop can have an airfoil shape.

Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine to define a bypass duct between the nacelle and the core engine, including a translating cowl moveable between a first position and a second position, a blocker door movable between a stowed position and a deployed position. The thrust reverser assembly includes multiple actuator assemblies to both translate the cowl and deploy the blocker door.

Abstract: An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.

Abstract: A gas turbine engine and thrust reverser assembly having a set of outer doors movable between a stowed position and a deployed position, where the set of outer doors extends outwards from the nacelle and a set of blocker doors movable between a stowed position and an deployed position, where the set of blocker door extends into an air flow conduit defined by the bypass duct to deflect air outwards.

Abstract: A turbine engine having an engine core, an inner cowl radially surrounding the engine core, an outer cowl radially surrounding the inner cowl and spaced from the inner cowl to form an annular passage between the inner and outer cowls that defines a nozzle, at least one control surface provided on the inner cowl and movable between a retracted position, where the nozzle has a first cross-sectional area, and an extended position where the nozzle has a second cross-sectional area that is less than the first cross-sectional area and an actuator operably coupled to the control surface and configured to move the control surface to control the cross-sectional area of the nozzle.

Abstract: A thermal insulation blanket assembly having a thermal insulation blanket including an aerogel insulation material having a first surface and a second surface that is oppositely-disposed from the first surface, a backing covering the second surface of the aerogel insulation material, and a skin layer covering the first surface of the aerogel insulation material.

Abstract: An acoustic liner and a method of attenuating noise are provided. The acoustic liner includes a face sheet, a back sheet spaced from the face sheet, and a core layer extending between the face sheet and the back sheet. The core layer includes a plurality of resonant cells, each resonant cell including at least one cell wall coupled to the back sheet along a cell wall base edge. The at least one cell wall extends from the back sheet at an angle toward the face sheet. The at least one cell wall further coupled to the face sheet along a cell wall top edge. The resonant cell is formed in a predetermined shape and contains a volume in a space defined by the at least one cell wall, the back sheet, and the face sheet. The cell wall base edge length is greater than the cell wall top edge length.

Abstract: An aircraft engine pylon having an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting and the upper panel, and tension fasteners at least partially coupling the upper fitting and the upper panel with the shear pin defining a shear force load path and the tension fasteners defining tension force load paths.