This composite material blade, which is formed using a composite material including reinforcing fibers and resin, and which has a positive pressure surface and a negative pressure surface, is provided with a ventral part, being the part on the positive pressure surface side in a blade thickness direction, which is the direction joining the positive pressure surface and the negative pressure surface, a dorsal part, being the part on the negative pressure surface side in the blade thickness direction, and a metal shield portion which is provided on the leading edge side, being the upstream side in a flow direction in which a fluid flows, wherein: the metal shield portion includes a main body portion provided on the leading edge side, and an embedded portion which is provided on the trailing edge side, being the downstream side in the flow direction, of the main body portion, and which is provided between the ventral part and the dorsal part; and the plate thickness of the metal shield portion in the blade thickness direction decreases from the main body portion toward the embedded portion.

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.

The disclosure relates to a ceramic matrix composite (CMC) aerofoil. Example embodiments include an aerofoil comprising first and second tubular CMC cores (302, 303) extending along a longitudinal axis of the aerofoil; and an outer CMC layer surrounding the first and second tubular CMC cores (302, 303) and defining an outer shape of the aerofoil having leading and trailing edges, wherein fibres within a wall of the second tubular CMC core extend to the trailing edge of the aerofoil.

An abradable coating structure with at least partially closed cells made of a metallic material with a mean cell wall porosity between 7 and 50%, in particular between 20 and 40%, a mean cell wall thickness between 50 and 200 m, in particular between 80 and 150 m, a cell size with a mean free diameter between 200 m and 15 mm, in particular 2 mm or in particular between 8 and 12 mm and a mean carbon concentration in the material of between 0 and 5% by weight, in particular between 0.05 and 2% by weight. The invention also relates to a component with a polyhedral cell structure and to a method for manufacturing the polyhedral cell structure.

A composite blade is formed by laying up composite material layers in which reinforcement fibers are impregnated with resin in a thickness direction of the blade. The composite blade includes a blade root on a base end side, an airfoil on a tip side, a first lay-up in which some composite material layers are laid up in the blade root so as to space parts of the composite material layers to form spacing parts and to extend from the distal toward the base end side in the thickness direction, and second lay-ups in which some composite material layers are laid up in the spacing parts so as to be lined up in the thickness direction. Among the second lay-ups, a second lay-up closer to a center side than to an outer side in the thickness direction is a larger distance from a proximal position to a top position.

A fan blade includes a blade body and a shape memory alloy actuator. The blade body has a pressure side disposed opposite a suction side. Each of the pressure side and the suction side extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge. The blade body defines a passageway that is disposed between the pressure side and the suction side. The shape memory alloy actuator is received within the passageway and is operatively connected to the blade body.

In some examples, an article may include a substrate and a coating system on the substrate. The coating system may include a layer comprising a plurality of voids, wherein respective voids of the plurality of voids define respective void volumes; and a nucleating agent within at least some of the respective void volumes of the layer, wherein the nucleating agent is configured to induce crystallization of the molten CMAS. The coating system may include an environmental barrier coating, thermal barrier coating, and/or abradable coating.

An apparatus relating to a rim seal for turbine engine comprising a wing and discourager extending into a cavity to form a labyrinth fluid path. The wing and discourager can each include a radial extension. Cooling air can pass through the rim seal along the labyrinth fluid path to resist the ingestion of hot gas from a mainstream flow.

The invention relates to a blade of a low-pressure compressor of an axial turbine engine. The blade comprises a vane in which a cavity is formed. The vane has a leading edge and a trailing edge, an intrados surface and an extrados surface which extend from the leading edge to the trailing edge, an outer casing which forms the intrados surface and the extrados surface and which delimits the cavity. The blade further comprises closed foam, such as a polymethacrylic foam, which blocks the cavity in order to isolate it from the environment of the blade. The blade further has a three-dimensional lattice which is formed in the cavity and which is integral with the vane of the blade. This barrier protects from chemical attacks and the introduction of impurities. The invention also relates to a production method for a hollow turbine engine blade which is filled with foam.

A centrifugal fan includes a motor, a support body, a rotating body, and a housing. The motor includes a rotor hub that rotates around a central axis extending up and down. The support body is fixed to the rotor hub and rotates together with the rotor hub. The rotating body is different from the support body in material. The rotating body is a continuous porous body. The housing accommodates the rotating body, the support body, and the motor. The housing includes an air inlet open in an axial direction and at least one air outlet open in a radial direction. A radially inner surface of the rotating body opposes a radially outer surface of the rotor hub with a gap interposed therebetween.