Abstract: A turbocharger includes: a bearing provided in a turbocharger body, and configured to rotatably support a turbine shaft in an insertion hole formed in the bearing; and an opposing portion which faces an end surface of the bearing in an axial direction of the turbine shaft. An end-surface guide portion is provided to any one of an opposing surface of the bearing which faces the opposing portion, and an opposing surface of the opposing portion which faces the bearing. The end-surface guide portion configured to make the insertion hole and an outer peripheral edge of the end surface of the bearing in radial directions of the turbine shaft communicate with each other extends forward in a rotational direction of the turbine shaft from a part of the end surface of the bearing which communicates with the insertion hole.

Abstract: The present invention relates to a spiral pump, including a support body; at least one or more substantially rigid rotary parts that are rotatable relative to said support body, wherein said one or more rotary parts comprise at least one integrated spiral fluid channel that has an inlet for receiving fluid arranged at or near the outer radial wall of said one or more rotary parts and an outlet for discharging fluid at an increased pressure at or near its rotary axis; wherein a fluid passage, configured for passing fluid at the increased pressure from inside the one or more rigid rotary parts to outside the one or more rigid rotary parts, is arranged at or near the rotary axis; and drive means for rotatably driving the one or more rotary parts. The invention further relates to a manufacturing method for such a spiral pump.

Abstract: An intershaft seal assembly including first and second or forward and aft carbon face seal rings supported on an annular housing and having first and second seal faces facing in opposite directions. Forward and aft springs operably disposed between housing and carbon face seal rings for biasing or urging carbon face seal rings in opposite directions. Annular forward and aft carriers mounted on and supported by annular housing and supporting carbon face seal rings. Forward and aft springs operably disposed between housing and the forward and aft carriers respectively. The springs may be wave springs. Inner and outer secondary seals may include inner and outer O rings disposed in annular inner and outer grooves in annular inner and outer surfaces in housing respectively and in sealing engagement with the forward and aft carriers. Carriers may be integral with carbon face seal rings in monolithic combined seal and carrier elements.

Abstract: The invention provides a drain to allow water to flow out of a pressure sensing line. The drain comprises a tube including a plurality of restrictors in flow series, each restrictor comprising a constriction whose internal diameter is less than the internal diameter of the tube.

Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.

Abstract: A turbine housing assembly seal can include a cylindrical portion that defines an opening having an axis where the cylindrical portion is disposed at a cylinder radius from the axis; a lower edge disposed at a lower edge radius that exceeds the cylinder radius; an sloped annular portion that extends radially inwardly from the lower edge; a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion; an upper bend that extends from an upper axial position of the cylindrical portion; and an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.

Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge flow in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion; a platform lip extending axially from the platform portion, the platform lip disposed radially outward from the at least one angel wing; and a plurality of turbulators disposed along and extending outward from the face of the shank portion between the platform lip and the at least one angel wing.

Abstract: A fan system may generate an air flow during use. In various implementations, a fan system may include a fan and an orifice. The orifice may include a converging section, a diverging section, and a minimum radius section disposed between the converging section and the diverging section.

Abstract: A method and system for controlling a pitch of blades of a fan assembly having a centerline axis of rotation is provided. The system includes a pitch change mechanism (PCM) including a hydraulic actuator positioned axisymmetric with respect to the fan assembly and configured to angularly displace the blades of the fan assembly between a first position and a second position. The PCM further includes a plurality of hydraulic fluid supply lines coupled in flow communication between the hydraulic actuator and a hydraulic fluid transfer sleeve, the hydraulic fluid transfer sleeve configured to transfer a flow of pressurized hydraulic fluid across a gap between a stationary member of the hydraulic fluid transfer sleeve and a rotatable member of the hydraulic fluid transfer sleeve.

Abstract: A fan case includes a composite fan case body including an outer surface and at least one attachment tool attached to the outer surface of the fan case body. The attachment tool includes a boss that has at least one fastener opening with a threaded insert. A channel extends from at least one interior cavity of the attachment tool through an outer wall of the attachment tool.

Abstract: A composite airfoil comprises a leading edge and a trailing edge, a pressure side and a suction side extending between the leading edge and the trailing edge, a tip at a radial outer end of the airfoil, a shank at a radial inner end of the airfoil, a dovetail connected to the shank, and a metal patch disposed between the dovetail and the shank.

Abstract: The present invention relates to a rotor arrangement for a turbomachine, having a rotor with a first rotor stage, a shaft, and a first hub for joining the first rotor stage to the shaft. The first hub has a balancing device for balancing the first rotor stage. In addition, the present invention relates to a compressor.

Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

Abstract: Systems, methods, and devices relating to a mechanism which can be used in gas cooling devices, pneumatic motors, turbines and other pressurized gas devices. A rotatable rotor is provided along with a number of hollow conduits that radially radiate from an exit port at the center of the rotor. The pressurized gas is injected into the mechanism at the inlet port(s). The gas enters the conduits and travels from the inlet port(s) to the exit port(s). In doing so, the gas causes the rotor to rotate about its central axis while the gas cools. This results in a colder gas at the exit port(s) than at the inlet port(s) due to an enhanced extraction of work, while maintaining a very low flow rate at the cold outlet.

Abstract: An aircraft turbine casing configured to carry a set of ring sectors that partly delimits a conduit inside which a gas flow passes through the turbine, including a dynamic mechanism adjusting radial position of ring sectors, an upstream radial lug that connects an upstream end of each ring sector to the casing, and a downstream radial lug that connects a downstream end of each ring sector to the casing. The upstream lug is made as a single piece with the casing and is directly connected to the upstream end of each ring sector.

Abstract: A mixed flow turbine wheel (1) for a turbocharger includes a hub (6) extending axially between a nose (10) and a partial back wall (9) defining an axis of rotation in the axial direction. The partial back wall (9) extends circumferentially from the hub (6) to an outer peripheral edge (11). A plurality of turbine blades (7) are coupled to the hub (6) and extended beyond the peripheral edge (11). The blades (7) are spaced circumferentially about the hub (6) at equal intervals around the axis of rotation. At least one scallop cut (5) is formed in the peripheral edge (11) at the partial back wall (9) for balancing the turbine wheel (1) about the axis rotation.

Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Abstract: A gas turbine engine includes a casing, a fairing, and a heat shield. The fairing is annularly shaped and disposed adjacent the casing. The heat shield is connected to the casing and includes a first portion and a second portion. The first portion is generally cylindrically shaped and extends between the fairing and the casing and the second portion extends generally radially away from the casing and the first portion toward the fairing.

Abstract: The invention relates to a guide means (10) for a gas turbine, in particular for an aircraft engine, having at least one casing element (12); having at least one first duct segment (14), which is arranged in the radial direction on the inside of the casing element (12), by means of which at least one duct (16), through which gas can flow, is at least partially delimited outward in the radial direction; having at least one second duct segment (26), which is arranged in the radial direction on the inside of the first duct segment (14), by means of which the duct (26) is at least partially delimited inward in the radial direction; and having at least one guide vane (28).