A variable geometry aerodynamic blade system employs a blade having a leading edge and a trailing edge. At least one shape memory alloy component is integrated in the blade for aerodynamic repositioning of one or both of the leading and trailing edges. At least one heating element interacts with the at least one shape memory alloy component to provide heating for transition between an austenitic and a martensitic phase. The at least one shape memory alloy component is responsive to the at least one heating element to alter one of a camber and twist of the blade responsive to a control signal. A control system is operatively engaged to the at least one heating element, the control system receiving a command signal and outputting the control signal responsive to the command signal.

Shape memory alloy (SMA) actuators and thermal management systems including the same. An SMA actuator includes an SMA lifting tube and a process fluid conduit configured to convey a process fluid through the SMA lifting tube. The SMA actuator assumes a conformation that is based on the temperature of the process fluid. The SMA lifting tube includes a first end and a second end configured to translate relative to the first end at least partially along a lateral direction. A thermal management system is configured to regulate a temperature of a process fluid. The thermal management system includes a heat exchanger that at least partially defines a heat transfer region, a process fluid conduit configured to convey the process fluid through the heat transfer region, and an actuator assembly including the SMA actuator. The actuator assembly is configured to selectively position the heat exchanger within a thermal management fluid flow.

An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.

A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.

A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.

A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a tip component removably connected to the blade body, the tip component formed of a second material that is different than the first material.

A blower assembly for advancing the flow of air in an air flow device at a selected one of a plurality of air flow rates. The blower assembly includes a blower housing defining a body thereof and a wall of the blower housing moveably secured to the body, a blower wheel rotatably mounted to the blower housing and a motor for rotating the blower wheel at a selected one of a plurality of rotational speeds. The blower assembly further includes a motion device secured to the body and to the wall. The motion device moves the wall relative to the body to a selected one of a plurality of distinct wall positions. The motor rotates the blower wheel at a selected one of a plurality of rotational speeds. A controller calculates an optimum wall position and rotational speed to provide for minimal energy usage rate.

A vibration mitigation coating for an integrally bladed rotor including a disk including an interior radius proximate an axis and an exterior radius distal from the axis, the disk including a substrate with an external surface, said external surface extends from the interior radius to the exterior radius; and a damping material disposed directly onto the external surface of the substrate.

A system for spacing and fastening tubular structures, and a related method. The system includes a spacer element configured to engage a plurality of tubular structures, to spatially separate the plurality of tubular structures from one another, and to distribute stress in the plurality of tubular structures. The system further includes a fastening element configured to extend around at least a portion of an outer surface of the plurality of tubular structures, and to fasten the plurality of tubular structures to the spacer element in an adaptively spaced configuration.

A component susceptible to the formation of deposits, such as a component of a hydrocarbon system in a gas turbine engine. The component includes a substrate having a surface susceptible to the formation of a deposit thereon. A shape memory alloy coating is formed on the surface of the substrate. The shape memory alloy coating is a plurality of particles formed on the surface, and each particle of the plurality of particles is formed from a shape memory alloy.