Abstract: A gas turbine engine includes a first case, a second case, and a fastener. The first case has a first flange defining a first opening. The second case has a second flange defining a second opening. The second flange abuts the first flange. The fastener extends through the first opening and the second opening. The fastener defines a first bore that extends through a fastener head along an axis towards an outlet port defined by a fastener shank.

Abstract: Systems and methods are disclosed for controlling the pitch angle of a propeller and rotor assembly that minimizes circumferential loads and stresses to a pitch angle control system. The system may generally include an annular actuator, load transfer bearing (LTB), and a guide shaft is pivotally attached to the LTB to direct the LTB along an arcuate path relative to a rotor frame.

Abstract: Systems and methods are disclosed for controlling the pitch angle of a propeller and rotor assembly that selectively limit the pitch angle according to a selected mode of operation. The system includes an actuator having forward and aft chambers, an oil transfer bearing (OTB), and a fine stop collar. The fine stop collar including a first passage in fluid communication with the OTB and forward chamber during a ground-based mode of operation, and a second fluid passage being in fluid communication with the OTB and forward chamber during a flight-based mode of operation.

Abstract: A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate including a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.

Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.

Abstract: A wind turbine includes a nacelle which houses components including a generator connected to a rotor. The nacelle includes a cover and a skeleton, the skeleton including a plurality of connected elongated skeleton members. The skeleton members include a first skeleton member, a second skeleton member non-parallel to the first skeleton member, and a bolt extending in parallel with the second skeleton member for connecting the second skeleton member and the first skeleton member. Also, a method is presented for removing a component housed in a nacelle of a wind turbine, including disconnecting a second skeleton member from first skeleton members, removing the second skeleton member from a path of removal of the component, and removing the component along the path.

Abstract: A sheet having a fan-mounting part for mounting a fan is provided. The fan includes a fan body including a cylinder part and a protrusion which is disposed on the cylinder part protruding in a direction substantially perpendicular to a side face of the cylinder part and an engaging member which is fitted on an outer side of the cylinder part and is thus attached to the fan body so as to be opposite the protrusion. The sheet having the fan-mounting part includes a sheet member and a non-stretchable flat ring-shaped reinforcing section. The sheet member has an open hole for receiving the cylinder part of the fan. The reinforcing section has an opening with substantially the same shape as an outer edge of the cylinder part of the fan.

Abstract: An impeller of a centrifugal fan includes multiple blades arranged annularly around a rotational axis, a main plate, a shroud, main plate-side welded portions between main plate-side blade axial ends of the blades and the main plate, and shroud-side welded portions between shroud-side blade axial ends of the blades and the shroud. The main plate is arranged opposite to main plate-side blade axial ends. The shroud is arranged opposite to shroud-side blade axial ends. The main plate-side welded portions have main plate-side welding holes that are recesses extending through the main plate to portions of the main plate-side blade axial ends. The shroud-side welded portions have shroud-side welding holes that are recesses extending through the shroud to portions of the shroud-side blade axial ends.

Abstract: A diffuser includes a lower element and an upper element. The upper element is fixed on the lower element, and the upper element and the lower element are formed separately. The lower element includes a lower inner wall and a lower outer wall, and the upper element includes an upper inner wall and an upper outer wall. The upper inner wall is connected to the lower inner wall to form an internal air-guiding surface, the upper outer wall is connected to the lower outer wall to form an external air-guiding surface, and the internal air-guiding surface and the external air-guiding surface define an air-guiding channel for air flow diffusion. The upper element includes an upper air-guiding wing for connecting the upper inner wall and the upper outer wall, and the lower element includes a lower air-guiding wing for connecting the lower inner wall and the lower outer wall.

Abstract: A device for automatic control of an angular position of turbine blades of a propeller device, in which the turbine blades are rotatable about a rotational axis and are pivotally displaceable about their respective pivot axes. The device includes a set of control blades kinematically connected with the turbine blades, said control blades are pivotally displaceable about respective pivot axes once the propeller device is exposed to a flow of fluid. The device further includes a transmission unit configured for transmitting pivotal displacement of the control blades to the turbine blades such that the turbine blades could be pivoted by the control blades. Pivoting of the turbine blades takes place simultaneously with the pivoting of the control blades. The angular disposition of the turbine blades is automatically set and remains invariant irrespective of direction of the flow of fluid.

Abstract: A fan has an impeller (20) that is equipped with blades (26, 28, 30, 32, 34; 58). The blades are configured so that the blade loading of individual blades differs during operation. As a result of this variable blade loading, the frequencies associated with the blade-passing noise (BPF) of the fan can be distributed over a broader frequency spectrum, and thus have a less obtrusive effect.

Abstract: An impeller includes a disk-shaped portion and rotor blades. The rotor blades include first rotor blades which includes a first curvature portion and second curvature portions. A center of a radius of curvature of the first curvature portion is on a first side. A center of a radius of curvature of each second curvature portion is on a second side. The radius of curvature of the second curvature portion radially outward is greater than the radius of curvature of the second curvature portion radially inward. The rotor blades include second rotor blades each of which is circumferentially between adjacent ones of the first rotor blades. Each second rotor blade includes third curvature portions. A center of a radius of curvature is on the second side. The radius of curvature of the third curvature portion radially outward is greater than the radius of curvature of the third curvature portion radially inward.

Abstract: An impeller in which blades and a shroud are bonded in a stable manner. The impeller is provided with a plurality of blades disposed on a base, and a shroud disposed facing the base across the blades. The shroud has a curved shape, wherein the shroud has a flat part in the outer periphery, protuberances are provided to flat surfaces of the blades, through-holes are provided to the flat part of the shroud, and, after the protuberances are inserted through the through-holes, the flat surfaces of the blades and the flat part of the shroud are bonded together by deforming the tips of the protuberances into thermally caulked parts larger in diameter than the opening diameters of the through-holes.

Abstract: In a featured embodiment, a fan rotor includes a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.

Abstract: A diffuser (10) comprises first (10.1) and second (10.2) annular portions bounded by forward (32) and aft (26) annular walls, wherein the first annular portion (10.1) is vaneless and radially within the second annular portion (10.2), and the second annular portion (10.2) is radially relatively compact and incorporates a plurality of vanes (48) with relatively high solidity, wherein the forward (32) or/and aft (26) annular walls is/are sloped so as to provide for meridional divergence within the second annular portion (10.2) of the diffuser (10), and the vanes (48) are shaped so as to substantially conform to the flow field within the second annular portion (10.2).

Abstract: Provided is a vacuum pump for preventing solidification of gas in a thread groove portion, and a heat insulating spacer used in the vacuum pump. The vacuum pump includes a heat insulating spacer that is interposed between a casing and an outer circumferential stator having a thread groove portion, supports the outer circumferential stator coaxially with a rotor in a rotor radial direction, with keeping a gap between the casing and the outer circumferential stator, and has lower thermal conductivity than the casing and the outer circumferential stator.

Abstract: A propeller pitch control actuation system includes a relatively lightweight, relatively inexpensive means for selectively preventing the propeller pitch control actuator from commanding reverse pitch positions.

Abstract: An air blower including a casing having an intake port and a discharge port an air-blowing fan disposed inside the casing to take in air through the intake port and discharge air from the discharge port; and a filter filtering the air taken in through the intake port, wherein an insect trapping part trapping an insect is disposed in a ventilation path between the intake port and the filter.

Abstract: A baffle assembly includes a collar with a port and a baffle positioned in the port. The baffle includes two ends, a hollow body, and a weld connecting the baffle to the collar, and the collar continuously surrounds the body of the baffle.

Abstract: A rotationally symmetrical part, such as a disk, for a turbine engine rotor. The part has a rotational axis (A) and includes, an annular row of teeth defining grooves therebetween for therein holding fir tree-shaped rotor blade roots. Each tooth includes a first side flank, having at least two projecting portions for holding a blade root and separated from each other by a hollow portion, and a second side flank including at least two projecting portions for holding an adjacent blade root and separated from each other by a hollow portion. Each tooth has, on substantially the entire longitudinal dimension thereof, a lack of symmetry in relation to a substantially radial median longitudinal plane. At least one of the circumferences of the projecting portions of the second flank is located between the circumferences of the projecting portions of the first flank and is radially shifted from the circumferences.