Abstract: A power takeoff and gearbox system of a multi-spool gas turbine engine includes a high rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, a first gearbox operably connected to the high rotor towershaft, a low rotor towershaft operably connected to and driven by a second spool of the gas turbine engine, and a second gearbox operably connected to the low rotor towershaft. The high rotor towershaft is located at a first case of the gas turbine engine and the low rotor towershaft is located at a second case of the gas turbine engine axially forward of the first case.

Abstract: A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.

Abstract: An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine.

Abstract: A method for monitoring a wind turbine comprises monitoring an acoustic signal and/or a vibrational signal within a tower of the wind turbine, analyzing the signal to identify one or more predetermined characteristic indicative of an event within the tower, recognizing the event has occurred based on the predetermined characteristic and generating an output based on the recognized event. The one or more predetermined characteristic being at least one of: an amplitude of the signal, a duration of the signal, a shape of the signal, one or more frequencies present in the signal and an energy of the signal.

Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.

Abstract: A wind turbine controller includes a thrust limiter for controlling the thrust of the blades of wind turbine using an estimate of the air density at the wind turbine. In one embodiment, the controller receives the blade flap load indicating the current load on one of the blades which varies linearly to the air density experienced by the wind turbine. In one embodiment, the controller determines the mean of a plurality of the blade flap load values measured during a predefined time period. Using a transfer function, the controller converts the mean of the blade flap loads to an estimate of the air density at the turbine. Generally, higher air density results in greater loads on the blades while lower air density results in lower loads on the blades.

Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.

Abstract: An induction heater is employed with a gas turbine engine in order to heat a static component of the gas turbine engine. The heating of the static component is performed prior to the ignition of the gas turbine engine and during transient conditions. This minimizes thermal differences between the components of the gas turbine engine during transient conditions to thereby increase the life span of the components.

Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The turbine blade includes a blade stem and the disk includes at least one mount post for mounting of the turbine blade. The retention assembly is secured with the disk by forming a diffusion joint with the disk.

Abstract: A hydraulically powered rotary actuator is described including: a hydraulic linear actuator which is moveable in both directions between a retracted position and an extended position; a clutch device which is operable between an engaged condition and a disengaged condition; and a rotary output member; wherein the linear actuator is coupled to the rotary output member by way of the clutch.

Abstract: Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric.

Abstract: A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

Abstract: A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.

Abstract: An assembly adapted for use in a gas turbine engine. The assembly includes a support component comprising metallic materials, a supported component comprising ceramic matrix composite materials, and an attachment pin configured to couple the supported component to the support component. The attachment pin includes compliant features to distributes loads applied to the supported component.

Abstract: A multilayer protective covering can protect a surface from lightning strikes. The covering includes a bottom conductive layer affixed to the surface and having a first opening that is aligned with a grounding connection so that the grounding connection is exposed through first opening and not in contact with the bottom conductive layer. The covering also includes a dielectric layer affixed to the bottom conductive layer and having second opening aligned with the grounding connection so that the grounding connection is exposed through second opening and not in contact with the dielectric layer. The covering additionally includes a top conductive layer affixed to the dielectric layer and covering the grounding connection. The top conductive layer directs electrical current from a lightning strike on the surface to the grounding connection.

Abstract: A fan blade apparatus for use in a high-volume, low-speed fan wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The fan blade coupled to an electric motor configured to rotate in an intended direction wherein the leading portion of the fan blade is at the forefront of the rotation of the blade. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The stepped configuration creates turbulent air flow when the electric motor rotates in the intended direction.

Abstract: A gas turbine engine for an aircraft including an engine core including a turbine, compressor, and core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; a gearbox that can receive input from the core shaft and can output drive to the fan at a lower rotational speed than the core shaft, an epicyclic gearbox including a sun gear, planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support. A first gearbox support shear stress ratio: torsional ? ? shear ? ? stress ? ? of ? ? the ? ? gearbox ? ? support ? at ? ? maxiumum ? ? take ? ? off ? ? conditions radial ? ? bending ? ? stiffness ? ? of ? ? the ? ? gearbox ? ? support is less than or equal to 4.

Abstract: Methods and systems are provided for preventing compressor surge while improving compressor efficiency and performance. In one example, a method may include a recirculation passage in a compressor configured with a casing treatment and the recirculation passage being cooled by a cooling jacket within the compressor housing wall. In another example, the recirculation passage includes guide vanes.

Abstract: The impeller has a bottom disk, a top disk, and impeller blades sandwiched between the two. The top disk has an inner opening edge that defines an axial inlet opening. The impeller blades have a first radial inward section that extends radially inward beyond the opening edge. A blade contour on each impeller blade points toward the inlet side of the impeller. The blade contour first radial inward section extends from a transition portion near the opening edge under the top disk. The blade contour on the first radially inward section of the impeller blade extends radially inward yond the opening edge and forms a specified formula geometrical edge design. A second portion of the impeller blades extends radially outward from the transition portion, the transition portion and the second portion of the impeller blade are covered entirely by the top disk from the first formula impeller blade contour.

Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.