Abstract: An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.

Abstract: A vane for a gas turbine engine includes a radially inner platform and a radially outer platform. At least two airfoils extend between the radially inner platform and the radially outer platform. At least two anti-rotation tabs extend axially from the radially outer platform.

Abstract: Nozzles and nozzle assemblies for gas turbine engines are provided. A nozzle includes an airfoil having an exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, an outer band disposed radially outward of the airfoil, the outer band including a radially outwardly-facing end surface, and an inner band disposed radially inward of the airfoil, the inner band including a radially inwardly-facing end surface. The nozzle further includes a flange extending radially from one of the radially outwardly-facing end surface or the radially inwardly-facing end surface. The flange is formed from a ceramic matrix composite material and includes a plurality of ceramic matrix composite plies stacked together and generally having an L-shape in a circumferential cross-sectional view.

Abstract: An exemplary section of a gas turbine engine according to this disclosure includes, among other things, a first array of airfoils including a first number of airfoils, and a second array of airfoils downstream of the first array of airfoils. The second array includes a second number of airfoils. The second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.

Abstract: A blading member for fluid flow machines, for example, gas turbine engines. The blading member includes a platform member, at least one airfoil member, and at least one interlock member.

Abstract: A spring damper includes a split ring body. The split ring body defines a center and a circular gap separating opposed first and second end portions of the split ring body. The first and second end portions are connected by a split ring body segment that is evenly spaced from the center. At least one of the first and second end portions is unevenly spaced from the center in relation to the segment that is evenly spaced with respect to the center.

Abstract: The present invention relates to a blade folding apparatus that may incorporate an overhead blade lifting system that reduces binding loads on blade pins induced by blade weight and pitch, and a folding mechanism that removes the necessity of personnel with external guide-poles to rotate main rotor blades. The apparatus may include flap locks, an overhead lifting system support structure attached to the flap locks, and two blade support beams to create and support a lifting point near each blade's longitudinal and lateral center of gravity. The blade support beams may be fitted with an articulation mechanism that lifts and/or lowers the overhead lifting structure. The apparatus facilitates rapid folding of the main rotor blades, and, when used with blade clamping mechanisms, is capable of aiding in the removal and/or the re-installation of the main rotor blades without external lifting mechanisms.

Abstract: A compressed air system contains a compressed air reservoir, a compressed air line system and a drive system connected on an inlet side to the compressed air reservoir by way of the compressed air line system. The drive system has a drive and a drive controller, the drive system has a valve provided so as to pneumatically separate the drive controller from the drive.

Abstract: An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge.

Abstract: When option attachment has not been attached, a reserve flow/direction control valve 8 is made to operate as a center bypass cut valve. When an option attachment has been attached, switching control is performed. In the switching control, when the option attachment is not used, the reserve flow/direction control valve 8 is made to operate as a center bypass cut valve for adjusting composite opening area of a center bypass and thereby controlling the flow rate of hydraulic fluid flowing into an actuator. When the option attachment is used, the reserve flow/direction control valve 8 is made to operate so as to supply the hydraulic fluid to an option hydraulic actuator 14.

Abstract: A method of charging a hydro-pneumatic energy storage system is described. The system has a first hydro-pneumatic accumulator with a first hollow vessel. Disposed within the first hollow vessel is a first compressible volume containing a first amount of gas. The system has a second hydro-pneumatic accumulator with a second hollow vessel. Disposed within the second hollow vessel is a second compressible volume containing a second amount of gas. The gas contained in the first volume is pre-pressurized to a first hydrostatic pre-charge pressure and the gas contained in the second volume is pre-pressurized to a second hydrostatic pre-charge pressure. The second pre-charge pressure is higher than the first pre-charge pressure.

Abstract: A hydraulic power tool includes a housing defining a cylinder, a piston at least partially positioned within the cylinder and movable between a retracted position and an extended position, a reservoir containing hydraulic fluid, a pump for transferring hydraulic fluid in the reservoir to the cylinder, causing the piston to move from the retracted position toward the extended position, a return valve defining a rotational axis and positioned between the cylinder and the reservoir, and a valve actuator driven by the pump for opening the return valve, thereby fluidly communicating the cylinder and the reservoir, in response to a predetermined pressure being reached in the cylinder.

Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.

Abstract: A sealing ring segment for a stator of a turbine, the sealing ring segment has substantially the shape of a cylinder casing segment and has on its outer side a groove for fixing a plurality of guide vanes. The sealing ring segment has, for each guide vane that is fixable to the sealing ring segment, at least one pressure bolt that acts on the respective guide vane by a restoring force, the pressure bolt being able to be fixed and accordingly oriented by a corresponding opening in the sealing ring segment and being configured as a cylindrical element which can be compressed in the axial direction, and wherein the respective pressure bolt has a disk spring and the restoring force of the respective pressure bolt acts in the radial direction with respect to the rotation axis of the turbine in which the sealing ring segment is placed.

Abstract: A motor casing is provided with a motor rib which is annularly formed along a circumferential direction of a fan while protruding toward a main shroud, and the motor rib is provided with a notch portion in a portion near a high-pressure region in a scroll chamber. A part of moisture flowing into the scroll chamber infiltrates into an inner peripheral space of the motor rib across the motor rib in a low-pressure region in which a flow velocity of ventilation air is high in the scroll chamber. However, the moisture is pressed to the notch portion by ventilation air infiltrating into the inner peripheral space of the motor rib from the low-pressure region in the scroll chamber, and is then discharged to the scroll chamber from the notch portion.

Abstract: A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Abstract: A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox.

Abstract: A turbine engine assembly and methods involving a turbine engine assembly are provided. In one method, the turbine engine assembly is received. The turbine engine assembly includes an annular stator vane structure disposed at a first orientation. The stator vane structure is reconfigured with the turbine engine assembly to be disposed at a second orientation.

Abstract: The present disclosure provides a variable compression ratio device including a piston, a piston pin, an eccentric cam, a connecting rod, a crank pin, a hydraulic pump, an oil jet injection nozzle, an oil jet control valve, and a control unit. In addition, a groove formed in a rotating direction of the eccentric cam is divided into a first chamber and a second chamber. The piston pin receives a hydraulic pressure through a path formed inside the crank pin and the connecting rod and receives the oil injected from the oil jet injection nozzle to control the hydraulic pressure supplied to the first chamber and the second chamber of the eccentric cam, thereby controlling the rotation position of the eccentric cam.

Abstract: A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform. The airfoil includes a ceramic-containing web that forms a portion of the airfoil and a metallic load shield that forms another portion of the airfoil.