A seal carrier for a turbomachine, in particular a gas turbine, including a carrier base and at least one seal member, the at least one seal member being connected to the carrier base, and the at least one seal member being formed by a plurality of cavities arranged adjacent one another, in particular in a regular fashion, in the circumferential direction and the axial direction, the cavities extending from the carrier base in the radial direction, is provided. At least one stiffening element on the carrier base, the stiffening element extending along the circumferential direction and at least partially covering the at least one seal member at one of its axial end regions is provided.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.

An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, a combustor module, and an exhaust module. The machine body comprises either one or two fluid inlet apertures. The or each fluid inlet aperture is configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan module, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module.

An exhaust device for a combined cycle power plant, includes a diffuser and a plenum. The diffuser includes a first wall, a second wall, a diffuser inlet, a diffuser outlet, and a diffuser flow path. The first and second walls extend circumferentially about a centerline axis of the exhaust device. The second wall is spaced from the first wall. The diffuser flow path is defined between the first and second walls, and extends from the diffuser inlet to outlet. The plenum includes an inlet wall portion and a non-circular plenum outlet, where the inlet wall portion is coupled to the diffuser outlet. The non-circular plenum outlet is spaced from the diffuser outlet along an axial direction of the exhaust device.

The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame. The filtration unit may include a positioning slot therein such that the positioning element extends through the positioning slot when the filtration unit is mounted within the holding frame.

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.

A turbine component includes: a metallic wall having opposed interior and exterior surfaces, the wall configured for directing a combustion gas stream in a gas turbine engine; and a metallic negative CTE structure rigidly attached to one of the surfaces.

A compressor wheel assembly (200) includes a compressor wheel (140) and a coupling member (230). The compressor wheel (140) is formed of a polymeric material. The compressor wheel (140) includes a hub (202), blades (204) extending from a forward surface (210) of the hub (202), and a shaft coupling portion (206) extending axially rearward from a rearward surface of the hub (202). The shaft coupling portion (206) includes a bore (208) extending therethrough and having a polygonal cross-sectional configuration. The coupling member (230) includes a head (232) and a body (234) extending axially from the head (232). The head (232) is received against a forward end (216) of the compressor wheel (140) and the body (234) extends through the bore (208). The body (234) has another polygonal cross-sectional configuration for transferring torque from the coupling member (23) to the compressor wheel (140).