A tie for a component includes a body including an elongate portion and an arch disposed adjacent to the elongate portion. The arch includes first and second middle surfaces extending between a pair of first and second outer curved surfaces, respectively. The body defines a minimum cross-sectional plane perpendicular to a longitudinal axis and passing through the elongate portion. The body further includes a minimum tie width at the minimum cross-sectional plane along a second transverse axis. The minimum tie width is greater than each of a first minimum arch width of the first middle surface and a second minimum arch width of the second middle surface by a width factor greater than or equal to 3 to less than or equal to 10.

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 disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud includes first and second walls that at least partially define a cooling core fluidly coupled to the cooling passage. The rotor blade also includes a plurality of ribs positioned within the cooling core and coupled to the first and second walls. The reinforcing structure includes a plurality of interconnected ribs having a first rib with a first orientation and a second rib with a second orientation. The first and second orientations are different in three spatial dimensions.

Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

A centrifugal fan assembly comprises a blade assembly integrally formed. The blade assembly comprises a plurality of blades integrally formed, wherein each blade of the plurality of blades has a twisted shape with a first portion of a hub end of the each blade facing a first adjacent blade, and a second portion of a outer end of the each blade diagonal to the first portion of the hub end facing a second adjacent blade, a fixing portion integrally connected to the blades. The centrifugal fan assembly comprises at least one opening formed in the fixing portion and a hub plate comprising a recessed portion and a convex portion enabled to couple to the blade assembly. The concave portion is provided to correspond to a shape of the fixing portion and the convex portion is provided to correspond to a shape of the at least one opening.

Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band. The radially inner end of the nozzle vane is attached to the arcuate inner band through an interlocking transition zone including a plurality of projections alternately extending from the radially inner end of the nozzle vane and the arcuate inner band, respectively, to undetachably couple the nozzle vane and the arcuate inner band. Optionally, the radially outer end of each nozzle vane is also attached to the arcuate outer band through an interlocking transition zone.

The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud includes first and second walls that at least partially define a cooling core fluidly coupled to the cooling passage. The rotor blade also includes a plurality of ribs positioned within the cooling core and coupled to the first and second walls. The reinforcing structure includes a plurality of interconnected ribs having a first rib with a first orientation and a second rib with a second orientation. The first and second orientations are different in three spatial dimensions.

A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.

Disclosed herein is a plurality of blades with a three-dimensional shape injection-molded at the same time, thereby reducing processes of manufacturing a centrifugal fan assembly. A centrifugal fan assembly includes a blade assembly formed by integrally injection-molding a plurality of blades where at least a part thereof is bent and a fixing portion, and a hub plate to which the fixing portion of the blade assembly is coupled, where the fixing portion includes at least one opening to allow extraction of the blade assembly from the mold.