An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.

An aircraft propulsion system apparatus includes a first skin, a second skin, an intermediate layer between the first skin and the second skin, a first cellular core and a second cellular core. The first cellular core is connected to the first skin and the intermediate layer. The first cellular core includes a plurality of first core chambers, where a first of the first core chambers is fluidly coupled with one or more first perforations in the first skin and one or more first perforations in the intermediate layer. The second cellular core is connected to the intermediate layer and the second skin. The second cellular core includes a plurality of second core chambers and a plurality of corrugations, where a first of the second core chambers is fluidly coupled with the first of the first core chambers through the one or more first perforations in the intermediate layer.

The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.

A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.

An acoustic core includes an array of resonant cells. The array may include a plurality of coupled resonant cells respectively defining an antecedent resonant space and a subsequent resonant space, with at least one cell wall having one or more wall-apertures defining a pathway between the antecedent resonant space and the subsequent resonant space. The array may include a plurality of high-frequency resonant cells respectively defining a high-frequency resonant space and being matched with respective ones of the plurality of coupled resonant cells. A cross-sectional dimension of the one or more wall-apertures defining the pathway between the antecedent resonant space and the subsequent resonant space may be less than a cross-sectional dimension of the antecedent resonant space and/or a cross-sectional dimension of the subsequent resonant space. The array may include a plurality of partitioned resonant cells that have a partition integrally formed with at least one of a corresponding one or more cell walls and transecting the corresponding resonant space with at least one surface of the partition having an interface angle that is oblique or perpendicular relative to a plane parallel to a top face and/or a bottom face of the array of resonant cells.

An inner barrel may comprise: a perforated top sheet; a backskin; a core disposed between the perforated top sheet and the backskin; and an insulator coupled to the backskin, the insulator comprising a polymeric material.

A method for manufacturing a thrust reverser blocker door may comprise thermoforming a sandwich panel comprising a facesheet, a backsheet, and a honeycomb core. The method may further comprising overmolding a mounting structure onto the backsheet. The first thermoplastic material may comprise a continuous fiber reinforced thermoplastic composite material. The second thermoplastic material may comprise a discontinuous fiber reinforced thermoplastic composite material.

An engine case is provided having a first solid wall region and a second solid wall region with an internal region between the first and second sold wall regions. The internal region defines at least one cavity. One or more lattice structures are provided within the cavity that controls the flow of coolant air through the cavity. The cavity may be divided into two or more distinct cooling regions for allowing particular coolant flow paths to be provided to different parts of the engine case.

A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is a unitary component and has a layered structure including a first layer at the first side of the plate, a second layer at the second side of the plate, and an intermediate layer between the first and the second layers.

A method for assembling a set including an inner wall, a shrouded outer wall and an intermediate element, each presenting substantially circular sections, the shrouded outer wall presenting a shape substantially complementary to a shape of outer and inner surfaces of the intermediate element, and whose inner surface covers the outer surface of the intermediate element. In particular, the method includes a step of placing a brazing sheet, whose melting temperature is lower than melting temperatures of other elements of the set, over an assembly surface in contact with another assembly surface, and a step of heating, by a furnace, a set including the outer or inner walls and the intermediate element between which is interposed a brazing sheet so as to fix the outer or inner wall by brazing on the intermediate element.