An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.

A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.

An electric power generation system receives a gas flow at a heater, heats the gas flow at the heater with a heated fluid from a waste heat process, and directs the heated gas flow to a turbine wheel of an electric generator. The heated gas flow drives rotation of the turbine wheel, and in response to rotating the turbine wheel, electrical current is generated by the electric generator. Generated electrical current is then directed to power electronics.

A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.

A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.

Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.

The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).

A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.

A first cylinder is configured to receive a gas turbine. A second cylinder surrounds an outer circumference of the first cylinder. Retainers extend from the second cylinder towards the first cylinder. Each of the retainers includes a central stalk that extends from the second cylinder towards the first cylinder and a branches extending radially from the central stalk.

A first cylinder is configured to receive a gas turbine. A second cylinder surrounds an outer circumference of the first cylinder. Retainers extend from the second cylinder towards the first cylinder. Each of the retainers includes a central stalk that extends from the second cylinder towards the first cylinder and a branches extending radially from the central stalk.