Abstract: Airfoils, additively manufactured airfoils, and methods of manufacturing airfoils are provided. For example, an airfoil comprises opposite pressure and suction sides that extend axially from a leading edge to a trailing edge and radially spaced apart inner and outer ends. The airfoil also comprises an outer wall defining the pressure and suction sides and leading and trailing edges. A rib extends within the airfoil from the pressure side to the suction side of the outer wall and radially from the inner to the outer end. The airfoil further comprises a first pre-impingement chamber surrounded by a first post-impingement chamber and a first dividing wall segment separating the first pre-impingement and first post-impingement chambers and having a plurality of cooling holes defined therein. The outer wall, rib, and first dividing wall segment are integrally formed as a single monolithic component.

Abstract: This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.

Abstract: A centrifugal compressor according to the present invention includes, as gas flow paths, diffuser flow paths into which process gas flowing from impellers to outside in a radial direction flows, curved flow paths that respectively communicate with the diffuser flow paths and change a flowing direction of the process gas from a direction toward the outside in the radial direction to a direction toward inside in the radial direction, and return flow paths that respectively communicate with the curved flow paths and cause the process gas flowing through the curved flow paths to flow into the impellers. In the present invention, the curved flow path configuring at least one of the gas flow paths is provided between a diaphragm and a flow path forming body that is provided between the diaphragm and the casing.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section. The fan has a fan diameter, Dfan, and the high pressure compressor section has a compressor diameter, Dcomp. The fan diameter Dfan and the compressor diameter Dcomp have an interdependence represented by a scalable ratio Dfan/Dcomp that is greater than about 4.5.

Abstract: A kinetic fluid energy conversion system comprises one or more hubs which rotate about a central hub carrier, each including one or more independently controlled articulating energy conversion plates (“ECP”). An articulation control system rotates each ECP independently of all others to control its orientation with respect to the fluid flow direction between an orientation of 90° perpendicular to the fluid flow, while traveling in the direction of the flow and 0° minimal drag parallel position to the flow, while traveling in the direction against the flow or blocked from it. Each hub can be operably coupled to another hub to form one or more counter-rotating hub and ECP assemblies whereby the mechanical energy is transferred through the hubs, to one or more clutch/gearbox/generator/pump assemblies thereby permitting such assemblies to be land-based when the system is air-powered, and above or near the surface, when the system is water-powered.

Abstract: A centrifugal compressor includes an electric motor coupled to a low-speed shaft, an impeller, and a speed increaser. The speed increaser includes a ring member, a high-speed shaft, rollers, a speed increaser housing member, a discharge passage, and a partition. The ring member includes a circumferential wall and is rotated when the low-speed shaft rotates. The high-speed shaft is coupled to the impeller. The rollers are located between the circumferential wall and the high-speed shaft. The speed increaser housing member stores oil. The discharge passage discharges oil out of the ring member. The partition is located between the speed increaser housing member and the circumferential wall in the radial direction. Power is transmitted from the low-speed shaft to the high-speed shaft by the ring member and the rollers.

Abstract: Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force.

Abstract: A turbine blade assembly may be provided for use in a gas turbine engine. The turbine blade assembly may include an airfoil and a tip shroud. The airfoil may extend radially outward from an axis of rotation of the airfoil. The tip shroud may be located at a radial end of the airfoil. The tip shroud may include a seal rail that extends in a direction of rotation of the airfoil. A notch, including a Z-notch or a V-notch, may be situated on a first side of the seal rail at an end of the seal rail. A variable fillet may be situated on a second side of the seal rail that is opposite of the first side on which the notch is situated. The variable fillet is a fillet having a curvature that varies along a length of the second side.

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.

Abstract: A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

Abstract: A gas turbine engine includes a low pressure compressor, a high pressure compressor, a turbine, and a gearbox. The high pressure compressor includes a plurality of stages split into a forward portion and an aft portion. One or both of the forward portion and the aft portion of the high pressure compressor are driven by the turbine through a gearbox such that the forward portion and the aft portion may rotate at different speeds.

Abstract: A fan is mounted on a fan shaft which constitutes part of a mainline shaft assembly centered for rotation on an engine axis X-X of a gas turbine engine. When in operation, the fan rotates about the engine axis X-X. A stub-shaft is arranged radially outwardly and concentrically with the fan shaft and adjoins an upstream facing face of a bearing sleeve. A fan catcher arm extends from the stub-shaft through the bearing sleeve and joins a fan catcher ring arranged downstream of the bearing sleeve and having an upstream facing face arranged to abut against a downstream facing face of the bearing sleeve in the event of a fan blade-off. Immediately downstream of the fan catcher ring is formed a shaft end which is configured to couple with an axially adjacent end of a low pressure compressor shaft. Immediately downstream of the bearing sleeve is a shaft end configured to connect with a turbine shaft.

Abstract: The invention relates to a rotating front part of an aircraft turbomachine intake comprising bolts for attaching a cone tip to an internal support, each bolt comprising a rear end that is screwed into the support and a front end that receives a clamping nut, a rotation-prevention portion of non-circular cross section of each bolt engaging with a hole of corresponding cross section of a rotation-prevention ring. Also provided are extraction bolts, of which a rear end is screwed into the filling piece, each bolt passing through a cone tip flange. Finally, the invention is configured such that, after removal of the nuts, forward tension on the bolts allows the removal of an assembly comprising the tip and the filling piece, while keeping the bolts screwed to the support.

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, 35% copper, 30.0-45.0% combined nickel, cobalt, and iron with combined iron and cobalt content at most one-third of the nickel content, 2.0-8.0% aluminum, and 5.0-15.0% chromium.

Abstract: A vacuum pump has, in at least either a stator disc to be disposed or a rotating disc to be disposed, a Siegbahn type molecular pump portion in which a spiral-shaped groove with a ridge portion and a root portion is engraved (disposed), and is structured to ensure high conductance at a returning flow channel formed at the outer periphery (outside) of the Siegbahn type molecular pump portion. This structure is created by a communicating portion (a groove portion, a slit) formed on each rotating disc, or an oblique plate disposed on the stator disc and the communicating portion formed on the rotating disc. The “communicating portion,” “groove portion,” and “slit” are configured to have “concave” shapes, a concave portion is provided by engraving a groove radially inward from an outer diameter portion (toward a side of a shaft of the vacuum pump) in the rotating disc (or stator disc).

Abstract: A yaw system for a wind turbine can have a yaw bearing with an outer bearing ring, an inner bearing ring, and a plurality of yaw rollers rotationally disposed between the outer and inner bearing rings so as to allow relative motion between the outer and inner bearing rings. A bi-directional braking assembly having an outer clutch ring attached to the outer bearing ring, an inner clutch ring attached to the inner bearing ring, and a plurality of brake rollers rotationally and slidably disposed between the inner clutch ring and at least one locking ramp adjacent the outer clutch ring. A plurality of spring members can extend from either ring projections or activation projections to each brake roller. An activation ring can slidably position the plurality of brake rollers into one of a locked position or unlocked position to prevent yaw rotation in an undesired direction.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes a seal segment. The seal segment includes a blade-sealing portion that provides an elongated slot, a flange that extends from the blade-sealing portion, and a hook that extends from the blade-sealing portion and is spaced from the flange. The hook has a surface that at least partially provides a cavity. A feather seal has an elongated portion and first and second legs which extend from the elongated portion. The first leg abuts the flange, the second leg is disposed in the cavity, and the elongated portion is disposed in the elongated slot.

Abstract: A guide vane for a diffuser of a radial compressor which is arranged downstream of a receiving area for a compressor wheel is disclosed. The guide vane has a skeleton line where the skeleton line is elliptical at least in a sub-region.

Abstract: A rotor blade rotated about a rotor hub is provided including a first section configured to mount to the rotor hub. The first section includes a spindle and an inboard torque tube surrounding a portion of the spindle. A second section of the rotor blade includes a flexbeam and an outboard torque tube attached to and surrounding the flexbeam. An inboard end of the flexbeam is rotatable coupled to a first end of the spindle. The second section is configured to rotate about a blade axis between an aligned position and a rotated position. A transitional brace configured to surround a portion of the rotor blade adjacent the coupled flexbeam and spindle is movable between a first position and a second position. When in the first position, the transitional brace limits movement of the second section about the blade axis.

Abstract: Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.