Abstract: An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.

Abstract: A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.

Abstract: One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector.

Abstract: A counter-rotating open-rotor blade aircraft propulsion system includes a structure supporting a plurality of blades. A rotor is drivingly coupled to the structure supporting the plurality of blades. The rotor includes a rotating coil disposed in the structure supporting the plurality of blades. A rotating magnetic field source includes two Halbach permanent magnet arrays.

Abstract: An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding.

Abstract: A metal matrix composite preform including an angled curved groove in the surface of the matrix material. A reinforcing fiber is placed within the angled curved groove and the stiffness of the fiber causes it to be pressed against an outer wall member defining the groove. The fiber is retained within the metal matrix composite preform prior to hot isostatic pressing.

Abstract: A method and device for coding and marking printing including defining a print image in dot formation of various sizes and locations; determining and providing a set of individual print control instructions for individually controlling a plurality of dot image print head nozzles to form the defined print image at absolute dot positions; and undertaking the individual control instructions to provide a printed image on a printing substrate corresponding to the defined print image, whereby the system allows for calculated adjustment of each dot position without computational limitation during the printing cycle.

Abstract: A method and system for carrying out vapor-phase lubrication of a component, such as a bearing for example, is disclosed herein. The method and apparatus can be applied to a turbine engine. The method includes the step of directing a first stream of fluid containing atomized lubricant to the component at a first velocity. The system provides a first fluid injection system for performing the first step. The system also provides a lubricant injection system communicating with the first fluid injection system upstream of the sump cavity and operable to atomize lubricant in the first stream. The method also includes the step of directing a second stream of fluid at a second velocity less than the first velocity to the component. The second stream is for controlling a temperature of the component. The system provides a second fluid injection system for performing the second step. Both of the directing steps are carried out concurrently.

Abstract: One form of the present invention contemplates an apparatus comprising a gas turbine engine core, a gearbox accessory mounted to the engine core and substantially enclosed by an inner fairing; a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing; and a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels.

Abstract: The mixing nozzle of the present invention generally includes a casing and mixer. The mixer fits within the casing and includes alternating elongated helical flow directing lands and notched barrier lands. The flow directing lands extend from the body and seal against the inside wall of the casing. The barrier lands also extend from the body but are offset from said inside wall of the casing. The flow directing lands and the barrier lands have differing helix angles and thus define alternating converging inlet channels and diverging outlet channels. Mixing of molten plastic is accomplished when the molten plastic is received from the inlet end of the mixing portion primarily by the inlet channels, passes over the barrier lands and through the notches in the barrier lands and passes primarily via the outlet channels through the outlet end of the mixer.

Abstract: Tank treads, brake linings, rifles stocks, and other devices requiring the bonding of metal to rubber, epoxy, or plastic, with a layer of metal foam interposed between the metal and the rubber or plastic.

Abstract: Tank treads, brake linings, rifles stocks, and other devices requiring the bonding of metal to rubber, epoxy, or plastic, with a layer of metal foam interposed between the metal and the rubber or plastic.

Abstract: A material for targets including a rubber skin material with an embedded wire skeleton, wherein the wire skeleton comprises a wire screen providing structural support for the rubber skin.