Ingrassia, Fisher & Lorenz UK Ltd

Heat resistant systems provide a self-activating insulative solution. A seal system (18) includes a case defining a joining line where two sections (70, 72) of the case join together. The case envelops an internal space (90) and separates the internal space from an external space. A seal (84) is disposed at the joining line (68) and a case extension (66) defines a cavity (116) on an outside of the seal. The case extension has an opening (114; 126; 128) that extends between the cavity and the external space. A lining (130) of a heat responsive material is provided in the case extension. The material expands to an activated state when exposed to heat above a threshold temperature and passes through the opening encapsulating the case extension and insulating the seal from the external space.

A composition includes:an adjunct ingredient chosen from a surfactant, a builder, a corrosion inhibitor, a chelating agent, and combinations thereof; anda carbonate inhibiting oligomer component comprising a compound (I) having the structure:wherein x is independently about 1 and/or 3.

Turbine components having cooling slots and methods of producing the same are provided. The turbine components include an airfoil (144) having a pressure side and a suction side (156,158), passages within the airfoil, and slots (160) open to the pressure side adjacent the trailing edge (147). The slots are in fluidic communication with the passages and configured to discharge a cooling fluid therefrom. The slots are defined by a slot upper side wall, a slot lower side wall, a pressure side surface, and a slot bottom. The pressure side surface includes a pressure side upper wall fillet coupled to the slot upper side wall and a pressure side lower wall fillet coupled to the slot lower side wall. Edges of the pressure side upper and lower wall fillets have a combined dimension equal to or greater than 30 percent of a total dimension of the pressure side surface.

A method and system for managing increases in electrical loads in an aircraft engine has been developed. First, demand for an increased electrical load for an electrical generator of the aircraft engine is detected. Notification of the demand for the increased electrical load is transmitted to the aircraft engine full authority digital engine control system (FADEC). The FADEC calculates the necessary power management adjustments to maintain aircraft engine turbine temperature and adjustments to the compressor variable vane and surge bleed valve schedules. The FADEC then commands the adjustment in the aircraft engine power setting parameter, compressor variable vane position, and surge bleed valve position.

Systems and methods are provided for promoting accurate data entry into flight systems during flight of an aircraft. The systems include a communication system configured to receive external information including user enterable information from at least one external source separate from the aircraft, an audio system configured to broadcast audible messages, and a controller configured to, by one or more processors, extract the user enterable information from the external information, generate and store expected data indicative of the user enterable information and an association with one or more avionics through which a user is able to input the user enterable information, detect a user interface interaction wherein the user is inputting information via the one or more avionics, and read aloud, via the audio system, the user enterable information in response to detecting the user interface interaction.

The invention relates to a method for plugging a formation in a subterranean zone, comprising (i) mixing alkali silicate and colloidal silica particles free of organic silane modification to form a composition; (ii) injecting the composition into the formation in the subterranean zone; and (iii) allowing the composition to be heated to a temperature of at least 40°C to below 90°C for a sufficient time so to form a gel that is impermeable to fluid flow. The invention further relates to the use of a composition comprising alkali silicate and colloidal silica particles free of organic silane modification for plugging a formation in a subterranean zone at a temperature of at least 40°C to below 90°C.

A magnetic rotating electric device that includes a stator and a rotor. The rotor is received within a central passage of the stator. An airgap is formed between the inner surface of the stator and an outer surface of the rotor. The rotor includes a plurality of spaced rotor magnets that are received within magnet pockets. Each magnet pocket includes a first open section and a second open section when a rotor magnet is received within the magnet pocket. The rotor includes an outer pocket forming portion for each magnet pocket that extends from the outer surface of the rotor to a first pocket side of an associated magnet pocket. The thickness of the outer pocket forming portion proximate first and second magnet ends of a magnet in a first open section and a second open section of an associated pocket is equal to a distance of the airgap.

A location of a vehicle is received from a geospatial sensor. Geographic locations of a plurality of external objects associated with the location of the vehicle are received from an external object source. Vehicle operator head position images are received from an operator monitoring system. A vehicle operator line of sight is identified based on the vehicle operator head position images. A subset of the plurality of external objects in the vehicle operator line of sight are identified. A projection angle is generated based on the vehicle operator line of sight and a location of a projection system. A command is issued to the projection system to display images of the subset of the plurality of external objects on a transparent retro-reflective display to align with the geographic locations of the subset of the plurality of external objects in accordance with the projection angle during operation of the vehicle.

A system is disclosed that provides a navigational display for an aerial vehicle. The system includes: a display device for the aerial vehicle; and a controller configured to generate a navigational display window configured to assist with landing operations. The navigational display window is configured to display on the display device: a view of an environment in front of the aerial vehicle; a landing target symbol that represents an intended landing location at which the aerial vehicle is intended to achieve a full stop above the intended landing location; and a real time stop indicator that indicates a predicted aerial vehicle stopping point if a current deceleration rate is maintained.

Aircraft systems and methods are provided for displaying attributes on a forward-looking graphical user interface display. An exemplary method involves determining candidate display positions for an attribute associated with a displayed object based at least in part on the geographic location and the altitude associated with the object, selecting, from among the candidate display positions, a visible display position for the attribute based at least in part on relationship between the visible display position and a reference display position for the attribute, and rendering a graphical representation of the attribute at the visible display position on the forward-looking graphical user interface display.