Abstract: Disclosed is a fairing element intended to be placed in a passage for flow of a fluid, in order to surround an obstacle which crosses the passage so that the fairing element guides the flow of the fluid on two opposite sides of the obstacle. The fairing element is designed such that the pressure of the flowing fluid is constant or approximately constant in an upstream part of the suction surface of the fairing element. A fairing element of this kind can be incorporated into a stator of a turbomachine, in particular of an aircraft turbomachine.

Abstract: A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (LT) along the axial direction, a circumference span (CS) along the circumferential direction, and a radial height (?rT) along the radial direction, and wherein these parameters are related by a tank sizing factor (TSF) equal to the effective length (LT) times the circumference span (CS) divided by the radial height (?rT) squared LT×CS/?rT2), wherein the tank sizing factor (TSF) is between 20 and 2200.

Abstract: A variable geometry turbine includes: a turbine rotor; a scroll passage forming part which forms a scroll passage; an exhaust gas passage forming part which forms an exhaust gas passage for introducing an exhaust gas from the scroll passage to the turbine rotor; and a variable nozzle unit including a plurality of nozzle vanes disposed in the exhaust gas passage and configured to be rotatable about respective rotation centers. The exhaust gas passage forming part includes: a first plate member having an annular first plate part; and a second plate member having an annular second plate part which defines the exhaust gas passage between the first plate part and the second plate part and is disposed closer to a turbine outlet than the first plate part in an axial direction of the turbine rotor.

Abstract: Provided is a vacuum blower, when used as a vacuum for sucking work, capable of increasing air flow with a larger volume of air sucked from a suction port and increasing the initial velocity (sucking rate) of sucked objects near the suction port, and when used as a blower for blowing work, capable of delivering rectilinearly directed wind from the blowing port and quickly switching between sucking work and blowing work. By sliding an inner pipe disposed inside a pipe relative to the pipe, opposite end portions of the inner pipe come into close contact with opposite end portions (turn portions) of a nozzle facing the opposite end portions of the inner pipe, such that one ejection port is closed and the other ejection port is opened to allow pressurized wind generated by a blower fan to be ejected along the inside of the inner pipe to switch between sucking state and blowing state.

Abstract: A turbine housing clamping connection for a turbine, and a turbine having a turbine housing clamping connection are described herein. The turbine housing clamping connection has a bearing housing, a turbine housing and a clamping component comprising a clamping flange clamped between a bearing housing clamping portion of the bearing housing and a turbine housing clamping portion of the turbine housing. The clamping flange has a bearing-housing-side clamping surface comprising a convexly curved clamping surface region. Furthermore, the convexly curved clamping surface region defines a minimum radius of curvature. A ratio of the minimum radius of curvature to an inner radius of the clamping surface is at least 0.1 and/or at most 10, and preferably at least 0.5 and/or at most 2.0, and more preferably at least 1.0 and/or at most 1.4.

Abstract: A unitized build assembly for a gas turbine engine includes an exhaust duct, a hot section with a locking structure and including a combustor and turbine section. The hot section at least partially circumferentially surrounds the exhaust duct. The build assembly includes a compressor section with an interface structure and is proximal to the hot section. The hot section at least partially circumferentially surrounds at least part of the compressor section and the locking structure is configured to engage the interface structure to limit movement of the hot section relative to the compressor section.

Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.

Abstract: An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

Abstract: A vortex generator for wind turbine blade is a vortex generator for wind turbine blade, the vortex generator being made of a resin, including: a platform; and at least one fin disposed projecting from an upper surface of the platform. The vortex generator includes a cavity that opens to a bottom surface of the platform and extends to an inside of the fin.

Abstract: A centering device (10) for centering a turbine housing (40) with respect to a central axis (33) of a radial turbine of a turbo system is described. The centering device (10) includes a ring-shaped body (11) having an outer diameter D1 and an inner diameter D2, wherein a ratio of D1/D2 is ?2. Additionally, the centering device (10) includes two or more centering elements (16) provided on a side surface (12) of the ring-shaped body (11) for engaging with respective complementary centering elements (21) provided on a bearing housing (20). The two or more centering elements (16) are configured for allowing a radial thermal expansion of the ring-shaped body (11) during engagement of the two or more centering elements (16) with the respective complementary centering elements (21). Further, a turbo system, including such a centering device as well as a method of centering a turbine housing are described.

Abstract: The present invention relates to a wind turbine blade (10) comprising an elongate reinforcing structure (62). The reinforcing structure (62) comprises a plurality of strips (63, 64, 65) of fibre-reinforced polymer arranged into adjacent stacks (66) of strips, and at least one alignment member (68). The latter comprises a plurality of alternating horizontal segments (70) and vertical segments (72), wherein a vertical segment of the alignment member is arranged between adjacent stacks of strips, and wherein a horizontal segment of the alignment member is arranged on top of or below each stack of strips. At least one of the vertical segments (72) comprises one or more apertures (84) for allowing resin to flow from one side of the vertical segment to the other side of the vertical segment.

Abstract: A pitch controlled wind turbine comprising a tower, a nacelle mounted on the tower, a hub mounted rotatably on the nacelle, and at least three wind turbine blades is disclosed. Each wind turbine blade extends between a root end connected to the hub via a pitch mechanism, and a tip end. The wind turbine further comprises at least three blade connecting members, each blade connecting member extending between a connection point on one wind turbine blade and a connection point on a neighboring wind turbine blade, the connection points being arranged at a distance from the root end and at a distance from the tip end of the wind turbine blade. The wind turbine further comprises at least three pre-tension members, each pre-tension member being connected to one of the blade connecting members and to a hub part, the pre-tension members thereby providing pre-tension in the blade connecting members.

Abstract: The present application provides a replaceable galvanic protection anode system for preventing and limiting the effects of liberation and damage to airfoils in a gas turbine, wherein turbine components are covered by a sacrificial material. The galvanic protection layer of the replaceable anodes may include a sacrificial material, such as aluminum, wherein the material provides corrosion resistance to the substrate. Additionally, the galvanic protection layer may include a sacrificial conductive material insert for increasing the conductivity of the sacrificial material and further improve the corrosion resistance of the replaceable anodes.

Abstract: A drain assembly includes a drain tube and a flapper assembly. The drain tube extends between a first tube end and a second tube end. The first tube end is configured to fluidly attach to an inlet plenum assembly of an engine system of a rotorcraft. The flapper assembly is positioned along the second tube end and comprises a flapper door that is configured to allow fluid to drain from the drain assembly to an engine compartment of the engine system of the rotorcraft. The flapper door is configured to prevent fluid, engine compartment gases, or flame from flowing into the drain assembly through the second tube end of the drain tube.

Abstract: The present disclosure discloses a hiding fan, the hiding fan includes a turntable, a plurality of fan blades, and a synchronization mechanism, the synchronization mechanism includes a rotation ring and a plurality of connection rods, the rotation ring is mounted on the turntable, the rotation ring can rotate relative to the turntable around a central axis of the turntable, each fan blade has an installation end and a free end, the installation end has an installation portion and a connection portion, the installation portion is mounted on the turntable through a first rotation connection portion, a first end of the connection rod is mounted on the turntable on the rotation ring through a second rotation connection portion, a second end of the connection rods is mounted on the connection portion, the fan blade can rotate around a central axis of the first rotation connection portion.

Abstract: A device, optimization method and system for cooperative matching of heat dissipation and noise are disclosed. A hood is mounted on a base, and a power device, a fan and a radiator are mounted in the hood; an output shaft of the power device is fixedly connected to a rotary shaft of the fan through a bearing pedestal to drive the fan to rotate, and the bearing pedestal is fixed on the base; the radiator is fixed on a radiator support, and a lead screw assembly is disposed on the base, and is used for changing the relative distance between the radiator and the fan; and a fan cover is mounted on a side, facing the fan, of the radiator, and a plurality of anemographs are disposed on the other side of the radiator, and a plurality of microphones are symmetrically disposed on two sides of the fan.

Abstract: A turbine engine comprising an engine core, a plurality of circumferentially arranged vanes, and a floating seal. The plurality of circumferentially arranged vanes forming an upper band and a lower band. The floating seal being carried by at least one respective vane of the plurality of circumferentially arranged vanes. The floating seal having a ring and at least one dynamic seal.

Abstract: The invention relates to a composite blade (5) for a turbine engine rotor, for example, an unducted propeller, comprising a skin (6) made of woven fibres forming the outer profile of the blade and an attachment (11) with cylindrical geometry in the direction of the span emerging from the blade root (9), which attachment is intended to retain the blade (5) on a hub of the rotor, characterised in that it further comprises a spar (16) having a hollow tube structure made of braided carbon fibres, fixed to the attachment (11) and extending inside the skin (6) over at least part of the span of the blade (5). The invention also relates to a propeller comprising said blade and to a method for manufacturing said blade.

Abstract: A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.

Abstract: A scroll structure of a centrifugal compressor includes, of a flow passage connection section where a scroll start portion and a scroll end portion of a scroll flow passage intersect, a connection region where a first inner circumferential surface of the scroll end portion in the centrifugal compressor and a second inner circumferential surface of the scroll start portion in the centrifugal compressor are connected. The connection region includes a turning start point where a direction starts to change from the first inner circumferential surface toward the second inner circumferential surface, and a turning end point where the change in direction from the first inner circumferential surface toward the second inner circumferential surface comes to an end.