Abstract: A brake disc of a rotor brake is provided including a generally cylindrical body having a first planar surface, a second, opposite planar surface, and a central opening extending there through. A plurality of first connection members extend generally outwardly from the first planar surface. The first connection members are generally equidistantly spaced about a diameter of the first planar surface. A plurality of second connection members extend generally outwardly from the second planar surface. The second connection members are generally equidistantly spaced about a diameter of the second planar surface.

Abstract: A brake disc of a rotor brake is provided including a generally cylindrical body having a first planar surface, a second, opposite planar surface, and a central opening extending there through. A plurality of first connection members extend generally outwardly from the first planar surface. The first connection members are generally equidistantly spaced about a diameter of the first planar surface. A plurality of second connection members extend generally outwardly from the second planar surface. The second connection members are generally equidistantly spaced about a diameter of the second planar surface.

Abstract: A gas turbine engine includes a compressor section, a combustor section and a turbine section, all arranged about a central axis. A turbine rotor drives a driveshaft for rotation on the central axis. The driveshaft in turn drives at least two fan rotors on axes parallel to, but spaced from, the central axis. The fan rotors each deliver a portion of the air they move into a central inlet for delivering the air to the compressor section. In addition, the majority of the air moved by the plurality of fan rotors passes between a cowl and an outer periphery of a housing for the central core of the engine. This bypass air provides propulsion as is known in the turbojet art.

Abstract: A sensor assembly for a gas turbine engine includes a telemetry module mounted at a rotor bearing compartment for sensing engine operational parameters and a cooling system for cooling the telemetry module separate from a rotor bearing lubricant flow.

Abstract: A gas turbine engine includes a compressor section, a combustor section and a turbine section, all arranged about a central axis. A turbine rotor drives a driveshaft for rotation on the central axis. The driveshaft in turn drives at least two fan rotors on axes parallel to, but spaced from, the central axis. The fan rotors each deliver a portion of the air they move into a central inlet for delivering the air to the compressor section. In addition, the majority of the air moved by the plurality of fan rotors passes between a cowl and an outer periphery of a housing for the central core of the engine. This bypass air provides propulsion as is known in the turbojet art.

Abstract: A sensor assembly for a gas turbine engine includes a telemetry module mounted at a rotor bearing compartment for sensing engine operational parameters and a cooling system for cooling the telemetry module separate from a rotor bearing lubricant flow.

Abstract: A blade for a turbine engine having a centerline. The blade comprises: a root section extending at an angle relative to the centerline; and an airfoil section extending from the root section. The root section is directly adjacent said airfoil section. In other words, the blade is neckless. The blade is part of a rotor assembly, and is preferably a fan blade.

Abstract: A blade for a turbine engine having a centerline. The blade comprises: a root section extending at an angle relative to the centerline; and an airfoil section extending from the root section. The root section is directly adjacent said airfoil section. In other words, the blade is neckless. The blade is part of a rotor assembly, and is preferably a fan blade.