A nested lattice structure 29 for use in a damping system includes a first lattice structure 26 including: a first outer passage 30 including a hollow interior 45; a second outer passage 32 including a hollow interior; and an outer node 42 including a hollow interior and forming an intersection of the first outer passage 30 and the second outer passage 32. The nested lattice structure 29 includes a second lattice structure 28 nested within the hollow interior of the first lattice structure 26 including: a first inner passage 44; a second inner passage 46; and an inner node 50 forming an intersection of the first inner passage 44 and the second inner passage 46. Each of the first inner passage 44, the second inner passage 46 and the inner node 50 are nested within the respective first outer passage 30, the second outer passage 32 and the outer node 42.

There is provided a seal assembly comprising: a first component and a second component spaced apart from the first component so as to define a passage for the transfer of fluid from an inlet of the seal assembly to an outlet of the seal assembly, wherein the first component comprises a concavity at least partially defining the passage, and wherein no part of the second component extends into the portion of the passage bounded by the concavity.

A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.

A method for producing a vibration-damping structure combination for damping vibrations for movable masses, having a first structure and a further structure, the further structure movable within a stop surface defined by a first structure surface of the first structure. The method includes a) providing the first structure, having the first structure surface and which defines a coating surface of a coating at least in some sections; b) coating the first structure surface of the first structure with the coating, the coating surface of the coating being applied such that a cavity is formed; c) filling the cavity with the filler; d) curing the filler until the further structure having a further structure surface is formed, which lies against the coating surface; and e) removing the coating, the further structure thus being movable relative to the first structure within the stop surface defined by the first structure surface.

A component for a turbine engine may be formed by spraying particulate with a nozzle toward a substrate. The particulate may be deposited to form one or more annular layers and a reinforcing structure. The component may be a closed loop annular component having a reinforcing structure of specific dimensions enabled by the methods described.

A noise attenuation panel for a structure within a propulsion system includes a first plurality of unit cells; and a second plurality of unit cells, the second plurality of unit cells merged within the first plurality of unit cells, the first plurality of unit cells including a first periodic structure having a first unit cell, a second unit cell, a third unit cell and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells.

A rotor shroud for a rotary machine in a cabin air compressor includes a disk portion centered on a central axis of the rotor shroud, a frustoconical portion extending from the disk portion, a flared portion extending from the frustoconical portion, and a variable lattice structure in an interior of the rotor shroud. The variable lattice structure includes a first region of the rotor shroud having a first lattice structure and a second region of the rotor shroud having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the rotor shroud.

A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.

Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the vane (14), the vane (14) further comprising an internal cavity between the lateral walls (15), which cavity is intended for passing a vane-cooling fluid, with a fluid inlet opening (19) opening through said first platform (12), characterized in that a gyroid surface network (18) fills at least part of the cavity, being arranged therein so as to guide the cooling fluid, and is in contact with at least part of the lateral walls (15).

A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.