A method for manufacturing a panel includes disposing one or several supports in a respective cavity(ies) in a honeycomb structure having a first skin and a second skin clasping the honeycomb structure. The supports are made of a fugitive material such as a thermoplastic and are auxetic so that, under the effect of an increase in temperature, their dimension between the first and the second skins remains below a predetermined value.

An acoustic liner that may be for a turbofan engine may comprise a first sidewall, a second sidewall, wherein the first sidewall and the second sidewall define a plurality of cells disposed therebetween, and a pre-cut septum ribbon comprising a plurality of permeable septum coupled together via a plurality of connecting members, with each one of the plurality of permeable septum being generally in a respective one of the plurality of cells.

A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.

A gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.

A propeller includes a rotatable hub and at least two propeller blades coupled to the rotatable hub. Each of the propeller blades is formed from a combination of a first material having a negative Poisson's ratio (NPR) and a second material having a positive Poisson's ratio (PPR). The first material and the second material can be layered or can be formed as a matrix with one of the first or second material embedded in the other. In a layered configuration, a layer of the first material is positioned between adjacent layers of the second material, and the layers can be connected by tabs of NPR material. The combination of the NPR and PPR materials improve the strength and impact resilience of the propeller blades compared to conventional materials.

Disclosed is a rotating component for a turbine engine including a first rotating component having a first snap surface and a second rotating component having a second snap surface wherein the first snap surface is configured to interlock with the second snap surface, and further wherein at least one of the first snap surface and the second snap surface have a friction enhancing material.

A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface.

A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.

A construction system for mechanical metamaterials based on discrete assembly of a finite set of modular, mass-produced parts. A modular construction scheme enables a range of mechanical metamaterial properties to be achieved, including rigid, compliant, auxetic and chiral, all of which are assembled with a consistent process across part types, thereby expanding the functionality and accessibility of this approach. The incremental nature of discrete assembly enables mechanical metamaterials to be produced efficiently and at low cost, beyond the scale of the 3D printer. Additionally, a lattice structure constructed of two or more rigid, compliant, auxetic and chiral part types enable the creation of heterogenous macroscopic metamaterial structures.

The present invention provides a shaped component for a compressor wheel that can be used to manufacture a turbo compressor wheel which is excellent in terms of high-temperature strength, rigidity, and dynamic balance and, furthermore, has optimal performance suitable for diverse required characteristics in individual portions. In the shaped component for an aluminum alloy turbo compressor wheel of the present invention, a continuous casting rod-shaped material having a small diameter or a forging-completed material obtained by carrying out hot closed die forging on the continuous casting rod-shaped material having a small diameter is used as a material, and the continuous casting rod-shaped material or the forging-completed material has a structure in which the average numbers of grain boundaries intersected in a circumferential direction on a transverse section orthogonal to a casting direction and a forging direction are minimized in a central portion and are maximized in an outer circumferential portion, and the casting direction and the forging direction of the material are along a rotational center axis line direction of a compressor wheel.