Abstract: A drive assembly for adjusting the pitch of a wind turbine blade comprises a stator having a cylindrical body and a drive member positioned at least partially within the cylindrical body and movable along an axis thereof. A mounting pin extends through an aperture in a wall of the cylindrical body for pivotally mounting the stator to a wind turbine structure.

Abstract: Aspects of the disclosure are directed to a gas turbine engine, having a fan that rotates about a central longitudinal axis. The gas turbine engine may comprise a nacelle having an outer wall that radially circumscribes the fan. The gas turbine engine may further comprise a fan drive gear system that drives the fan, and a rotating shaft that is coupled to and drives the fan drive gear system. The gas turbine engine may further comprise an air vent line in fluid communication with a bearing compartment to remove air from the bearing compartment and provide the removed air to a deoiler that removes oil droplets from the removed air and provides deoiler filtered air. A vent output line receives the deoiler filtered air and discharges the deoiler filtered air along a radially interior surface of the nacelle outer wall.

Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. Each of the plurality of blades includes a root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the blades to define a boundary of a flow path of the gas turbine engine.

Abstract: A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion.

Abstract: According to one embodiment, a fastener installed between a blower fan and a rotating mechanism includes a fastener main body, a first flange portion, a second flange portion, and a slit portion. The fastener main body has a cylindrical outline which is partly cut. The slit portion is continuously cut from the first flange portion to the second flange portion via the fastener main body.

Abstract: The present disclosure is directed to an outer drum rotor assembly for a gas turbine engine including a first outer drum and a second outer drum. Each outer drum defines a radially extended flange adjacent to one another. A plurality of outer drum airfoils is extended inward along the radial direction from between the first outer drum and the second outer drum at the flange.

Abstract: A component for a fluid flow engine, such as a gas turbine, includes a first side, e.g. a top side and a second side, e.g. a bottom side, wherein the component further includes a mesh of interior channels for guiding a fluid through the component, wherein a fluid inlet being in fluid communication with channels of the mesh is provided at the first side and at the second side, respectively, and wherein the mesh is further arranged and configured such that channels originating from the fluid inlet of the first side and channels originating from the fluid inlet of the second side are interlaced such that a fluid entering the component is at least partly guided according to opposing directions in the mesh.

Abstract: An exemplary carbon seal assembly generally may include a stator fixable to a static component, such as a mechanical housing of a gas turbine engine, and a rotor fixable to a rotating component, such as a shaft of the gas turbine engine, where the rotating component is rotatable relative to the static component. The carbon seal assembly may also include a carbon ring and a spring attached thereto positioned between the stator and the rotor, where the spring may be configured to move the carbon ring fore and aft between the stator and the rotor. The carbon seal assembly may further include a diaphragm operatively attached to stator and to the carbon ring and spring combination.

Abstract: A fan housing includes a housing body for accommodating fan components and an outer casing which surrounds the housing body in circumferential direction. The housing body has at least two webs extending in a circumferential direction on the radial outer side. The outer casing has at least two ribs extending in the circumferential direction on the radial inner side. The ribs, in the assembled state, between the housing body and the outer casing, form a channel circulating in the circumferential direction for receiving and holding a heating band. The outer casing has at least one guiding rib directed in the radial direction toward a housing body as well as into the channel and extending in the circumferential direction.

Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion with a constant cross-sectional area and a cross-sectional shape having a maximum height that is offset relative to a longitudinal centerline of the metering portion; and a diffuser portion extending from the metering portion to the external surface of the body.

Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.

Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: To provide a vacuum pump capable of heating only a flow channel extending from the vicinity of an exit of a thread groove exhaust flow channel toward an outlet port and prevents the accumulation of a product that is caused by a decrease in the temperature of process gas near the exit of the thread groove exhaust flow channel and the flow channel. A vacuum pump has a thread groove exhaust portion that has thread groove exhaust flow channels at least in respective parts of portions on inner and outer circumferential sides of a rotor (rotating body), a casing enclosing the thread groove exhaust portion, an outlet port for exhausting gas compressed by the thread groove exhaust portion to the outside of the casing, and a partition wall that covers a flow channel extending from the exits of the thread groove exhaust flow channels toward the outlet port.

Abstract: The present disclosure concerns a fastening strut for a fan guard with at least one first leg extending in a longitudinal direction, configured so as to reach across several cage bars of the fan guard, wherein the at least one first leg comprises a free lengthwise end, and in the region of the free lengthwise end of the at least one first leg a cube-shaped or cuboidal fastening element is secured laterally to the at least one first leg by integral bonding in a transverse direction running perpendicular to the longitudinal direction.

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

Abstract: A heat sink that can be positioned around a rotating shaft includes a cylindrical body with a first end and a second end, a bore running through the body with a first opening at the first end of the body and a second opening at the second end of the body, fins extending radially outward from the body and running from the first end to the second end of the body, and channels defined between the fins and running from the first end to the second end of the body.

Abstract: The invention relates to an axial ventilator comprising an external or an internal rotor motor that has a rotor (1), at least two blades (4) with end-side connection regions (6) being connected form- and force-fittingly to said rotor (1) and this connection being achieved by bracing said connection regions (6) using a clamping ring (2). The invention is characterised in that said clamping ring (2) comprises recesses (5) that correspond to the number of blades (4) and form, together with one retainer piece (7) in each case, receiving portions (8) for the connection region (6) of the blades (4), said retainer piece (7) being supported against the rotor (1) and the clamping ring (2) being connected, with the inclusion of the connection region (6) of the blades (4), to said rotor (1), preferably to a flange (3) formed on the rotor (1) or to a hub (9), etc.

Abstract: A support system for a gas turbine engine is provided. The support system includes a load-bearing unit that includes a first flange, a support element supporting the load-bearing unit and having a second flange, a fastener connecting the first flange and the second flange, a first super-elastic shape memory alloy component in contact with the first flange, and a second super-elastic shape memory alloy component in contact with the second flange. The first and the second super-elastic shape memory alloy components are configured to deform when a load exerted by the fastener exceeds a threshold load value of the fastener.

Abstract: A turbine unit for a hydraulic installation, and more in particular it deals with the hub of the turbine unit. The present invention proposes to provide means for adjusting a gap extent formed between the hub and the inner edge of the blade, this way dramatically increasing the performance of the turbine.

Abstract: A system for cooling a tower of a wind turbine including at least one cooling fluid inlet arranged in a tower wall for receiving a cooling fluid into the tower, a filtration assembly arranged within the tower, and at least one cooling fluid outlet for directing the filtered cooling fluid within the tower. The filtration assembly including a plurality of flow guiding structures that define a plurality of flow paths for providing a plurality of flow direction changes and/or flow velocity changes to the cooling fluid.