Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

Abstract: A method of on-demand energy delivery to an active suspension system comprising an actuator body, hydraulic pump, electric motor, plurality of sensors, energy storage facility, and controller is provided. The method comprises disposing an active suspension system in a vehicle between a wheel mount and a vehicle body, detecting a wheel event requiring control of the active suspension; and sourcing energy from the energy storage facility and delivering it to the electric motor in response to the wheel event.

Abstract: A method and system for measuring rotor position or velocity in an electric motor disposed in hydraulic fluid. The system comprises a contactless position sensor that measures electric motor rotor via magnetic, optical, or other means through a diaphragm that is permeable to the sensing means but impervious to the hydraulic fluid. An electronic sensor is positioned outside the operating fluid, whereas the motor is located in the fluid volume.

Abstract: An exhaust section of a gas turbine engine includes an exhaust plug, and an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. The exhaust plug is configured for axial translation relative to exhaust nozzle between a first position and a second position to selectably change a cross-sectional area of the exhaust pathway during thrust reversal operation of the gas turbine engine to reduce an amount of reverse thrust necessary. A method of operating a gas turbine engine includes actuating a fan thrust reverser to divert a fan airflow from a fan airflow pathway, and translating an exhaust plug from a first position to a second position, thereby increasing a cross-sectional area of an exhaust pathway to reduce an amount of reverse thrust necessary.

Abstract: Embodiments of the present disclosure include systems and methods for implementing an Iconizer in a cloud-based platform such as cloud based platform (e.g., cloud-based collaboration platform or cloud-based platform providing collaborative and/or file sharing services). The iconizer can facilitate the display on a graphical user interface (GUI) of certain features of the storage operation and synchronization to a user. Some embodiments contemplate methods for representing Unicode text in the file system operations in either Normal Form Composed (NFC) or Normal Form Decomposed (NFD). Various disclosed embodiments facilitate operations using either or both formats, or a combination of the two.

Abstract: Various embodiments related to hydraulic actuators and active suspension systems as well as their methods of use are described.

Abstract: A bicycle safety device includes an elongated support pole having a connection unit along a bottom end, and an illumination unit along the top end. The connection unit includes any number of clamps or brackets for securing the device onto a bicycle. The illumination unit includes any number of lighting elements for producing continuous or flashing beams of visible light 360 degrees about the pole. A power unit provides the necessary power requirements to the lighting unit. A light shield is positioned beneath the illumination unit, and a spring is positioned between the pole and the connection unit.

Abstract: A nacelle for a gas turbine engine includes a upper and lower bifurcations, an inner diameter cowl and a first latch system. The inner diameter cowl extends between the upper and lower bifurcations and the first latch system is mounted on the inner diameter cowl. The first latch system is spaced along the inner diameter cowl between the upper and lower bifurcations.

Abstract: A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame. The castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure.

Abstract: A method of on-demand energy delivery to an active suspension system comprising an actuator body, hydraulic pump, electric motor, plurality of sensors, energy storage facility, and controller is provided. The method comprises disposing an active suspension system in a vehicle between a wheel mount and a vehicle body, detecting a wheel event requiring control of the active suspension; and sourcing energy from the energy storage facility and delivering it to the electric motor in response to the wheel event.

Abstract: Various embodiments related to hydraulic actuators and active suspension systems as well as their methods of use are described.

Abstract: A core compartment ventilation device is provided. The core compartment ventilation device comprises a fireproof sealing member for substantially sealing a core compartment in a nacelle for a gas turbine engine and a chimney configured to be in fluid communication with the fireproof sealing member for conducting hot air from the core compartment to the external atmosphere via the fireproof sealing member. A gas turbine engine and nacelle including the core compartment ventilation device are also provided.

Abstract: A method of on-demand energy delivery to an active suspension system comprising an actuator body, hydraulic pump, electric motor, plurality of sensors, energy storage facility, and controller is provided. The method comprises disposing an active suspension system in a vehicle between a wheel mount and a vehicle body, detecting a wheel event requiring control of the active suspension; and sourcing energy from the energy storage facility and delivering it to the electric motor in response to the wheel event.

Abstract: A nacelle assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan nacelle bounding a bypass flow path. The fan nacelle includes a first nacelle section and a second nacelle section. The second nacelle section includes a moveable portion movable relative to a forward portion to define a secondary flow passage. The first nacelle section includes an inlet lip. A thrust reverser is configured to selectively communicate a portion of bypass airflow between the bypass flow path and the secondary flow passage. A pump is configured to selectively communicate airflow between the inlet lip and the secondary flow passage. A method of flow distribution for a gas turbine engine is also disclosed.

Abstract: A thrust reverser cascade for a gas turbine engine is disclosed. The thrust reverser cascade may comprise a plurality of turning vanes. One or more of the turning vanes may comprise a core formed from a polymer and a metallic coating applied to at least a portion of an outer surface of the core. The metallic coating may comprise nickel or a nickel alloy.

Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a base member, and a retaining member at least partially defining a first aperture and a cavity. The pivot is configured to extend at least partially into the first aperture. The cavity is configured to accommodate a portion of the link arm.

Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a retaining member having a first end and a second end and defining a first aperture and a cavity, wherein the pivot is configured to extend at least partially into the first aperture and the cavity is configured to accommodate a portion of the link arm, and wherein the retaining member comprises an attachment aperture located at the first end and a lip extending from the retaining member at the second end, the attachment aperture configured to receive a fastener and the lip configured to be placed under a distal layer of an inner fixed structure (IFS).

Abstract: A fan duct seal for a gas turbine engine has at least one seal body with a hollow center. A first opening is formed in the seal body that is in fluid communication with the hollow center. The first opening is configured to receive fan air flow. A second opening is formed in the seal body that is in fluid communication with the hollow center such that cooling flow enters the first opening, moves through the seal body and exits from the second opening. A fan duct for a gas turbine engine and a method of cooling a fan duct seal assembly are also disclosed.

Abstract: Systems for thrust reverser link arm connections are described herein. A linkage system for a nacelle may comprise a thrust reverser link arm and a fitting. The fitting may comprise a base plate configured to be fastened to a proximal surface of an inner fixed structure (IFS), a first wall extending orthogonally from the base plate, a second wall extending orthogonally from the base plate, and a pin extending orthogonally from the first wall and extending orthogonally from the second wall. A first end of the thrust reverser link arm may comprise a removable member, the removable member having an inner surface comprising a semi-circle, the inner surface configured to seat against the pin. The removable member may be removed from the linkage system from a radially outward side of the IFS.

Abstract: Systems for thrust reverser link arm connections are described herein. A fitting for a thrust reverser link arm may comprise a base plate configured to be fastened to a proximal surface of an inner fixed structure (IFS), a first wall extending orthogonally from the base plate, a pin extending orthogonally from the first wall, a second wall extending orthogonally from the base plate, a removable member, a first column located between the first wall and the second wall, and a second column located between the first wall and the second wall. The removable member may surround at least a portion of the pin. The removable member may be removed from a radially outward side of the IFS.