Abstract: A method and mould system for manufacturing at least a root section of a wind turbine blade is described. The method and system utilise a mould inlay which is arranged on top of a mould surface of a mould part so as to change the radius of curvature of the mould part and thereby also the diameter of a root section manufactured via the mould part and mould inlay. Further, blades manufactured via the method and mould system are described.

Abstract: A gas turbine engine includes a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is positioned radially outwardly of the radially outer tip of the turbine blade. The blade outer air seal has a forward hook at an axially forward location and an aft hook at an axially aft location. An axial direction is defined by a rotational axis of the turbine blade. The blade outer air seal has a central web extending axially between the forward and aft hooks. The forward and aft hooks extend generally radially outward from the central web, and have slots for being received on forward and aft support hooks of a blade outer air seal support.

Abstract: A compressor scroll (1A) is provided with: a scroll-flow-path formation part (8A) that forms a scroll flow path; and an outlet-flow-path formation part (9) that is connected to a winding-end section (11) of a scroll flow path (8a) and that forms an outlet flow path (9a) extending in a direction tangential to a circle around an axis (O), wherein, at least at the winding-end section (11) in an area where a winding-start section (10) intersects with the winding-end section (11), the scroll-flow-path formation part (8A) is provided with a bulging part (15A) that bulges the scroll flow path in the radial direction toward the side where the winding-start section (10) is present.

Abstract: A ventilator unit has a ventilator housing and at least one ventilator accommodated in the ventilator housing. A first outlet guide apparatus is associated with the ventilator and is arranged in the ventilator housing, wherein the first outlet guide apparatus has first outlet guide vanes distributed circumferentially. A second outlet guide apparatus is correlated with the first outlet guide apparatus and arranged in a flow path of an air stream sucked in by the ventilator. The second outlet guide apparatus is connected to a protective screen. The second outlet guide apparatus has second outlet guide vanes. The second outlet guide apparatus increases the throw of the ventilator unit.

Abstract: Impeller for a radial fan, the impeller comprising a front side, a rear side and a peripheral edge, a hub element, an annular covering disc positioned on the front side, an intake opening formed on the front side, a support disc positioned on the rear side, blades extending substantially radially from the hub element towards the peripheral edge, and outflow openings formed in the region of the peripheral edge. A first outer diameter of a radially outer edge of the annular covering disc is greater than a second outer diameter of a radially outer edge of the support disc. Openings are formed in the annular covering disc, wherein the openings are positioned between the radially outer edge of the annular covering disc having the first outer diameter and a radially inner edge of the annular covering disc having a first inside diameter.

Abstract: An axial fan wheel, in particular for the radiator of a motor vehicle engine, is described. The axial fan wheel includes a crown ring having a multiplicity of rotor blades, a hub having an inner ring which is connected or connectable to a drive shaft, and having, for the purpose of torque transmission, connection surfaces along an outer periphery of the hub which are connected to the inner ring and to the crown ring. The hub has through-passages between the inner ring and the outer periphery. At least one element, arranged rotationally fixedly on the axial fan wheel inside the crown ring, is designed to maintain a pressure difference in the axial direction when the axial fan wheel rotates.

Abstract: A centrifugal compressor impeller (60; 160) has a hub (62; 162) having a gaspath surface (64; 164) extending from a leading end to a trailing end. A plurality of blades (70A, 70B; 170) extend from the hub gaspath surface and each have: a leading edge (72A, 72B; 172); a trailing edge (74A, 74B; 174); a first face (80A, 80B; 180); a second face (82A, 82B; 182); and a tip (78A, 78B; 178). A plurality of flow splitter segments (120, 122; 320, 322) extend between associated twos of the blades and each spaced from both the hub gaspath surface and the tips of the associated two blades.

Abstract: An applicator tool (40) for repairing damage (26) to a wind turbine blade (20) includes a spatula (42) including a flexible extrusion plate (44) and one or more spacers (60, 106) positioned proximate an inner surface (58) of the extrusion plate (44). The one or more spacers (60, 106) are configured to define a gap between an outer surface (34) of the wind turbine blade (20) and the inner surface (58) of the extrusion plate (44). A feed tube (86) is provided for supplying a coating material to the spatula (42), wherein the spatula (42) is configured to shape the coating material into a coating (30) over a damaged area (26) of the wind turbine blade (20).

Abstract: Inner covering for wind turbine blades and method for mounting same, wherein said covering consists of a wall cover with a flexible wall which is formed based on layers of composite materials, having shapes and dimensions being approximately the same as those of the inner area of the blade structural element, said cover being mounted on a support with which it is introduced inside the blade. Between the support and the cover, an inflatable chamber is arranged, which upon being inflated causes the cover to be compacted and adhered against the inner surface of the blade structural element.

Abstract: The invention relates to a wind power installation comprising a rotor (6) which can be turned with wind power, and has a rotor hub (10) and at least one rotor blade (11) rotatably mounted thereon, a higher-level operation control device (15) and a blade angle adjustment system (16) communicatively connected to same and having components that can be used for the emergency deactivation of the wind power installation, by means of which system the rotor blade (11) can be rotated relative to the rotor hub (10) and can be thereby positioned in different blade angle positions, wherein control commands (54) for the positioning of the rotor blade can be output to the blade angle adjustment system (16) by the operation control device (15), and the blade angle adjustment system (16) follows the control commands (54) in a normal operation of the wind power installation and correspondingly positions the rotor blade (11), and wherein the blade angle adjustment system (16) also has a monitoring unit (50) that can run in par

Abstract: The invention concerns a method for controlling a control valve (20) of a turbomachine operating at an engine speed at a cruise value (Vc) and oscillating around the cruise value (Vc) of same, the method being implemented by a calculation unit (40), and being characterised in that it comprises a step of determining a position control for the control valve (20), filtered of the oscillations of the engine speed around the cruise value (Vc).

Abstract: A wind turbine blade having a surface mounted device attached thereto via at least a first attachment part, which is connected to a part of the device. The first attachment part comprises an outer attachment part providing a first bonding connection between the device and the surface of the blade, wherein the first bonding connection is an elastic bond, and an inner attachment part providing a second bonding connection between the device and the surface of the blade, wherein the second bonding connection has a structural bond. The structural bond prevents the surface mounted device from creeping and the elastic bond region relieves stresses on the bond line, such as peel stresses, whereby the surface mounted device is less likely to be ripped off the surface of the blade due to forces affecting the device or the blade.

Abstract: An exhaust hood in an embodiment includes: an outer casing; and an annular diffuser which is provided on a downstream side of a final turbine stage and formed by a cylindrical steam guide and a cylindrical bearing cone provided inside the steam guide. The steam guide includes a curved guide and a flat-plate guide which is provided on a downstream side of the curved guide. When a cross section of the outer casing vertical to the rotation axis of the turbine rotor is viewed from the downstream side of the steam guide, expansion outward in the radial direction of the flat-plate guide is set based on D/H where a distance between the rotation axis of the turbine rotor and an inner surface of the outer casing is H and a distance between the rotation axis of the turbine rotor and a downstream end of the flat-plate guide is D.

Abstract: An axial fan wheel, in particular for the radiator of a motor vehicle engine, is described. The axial fan wheel includes a crown ring having a multiplicity of rotor blades, a hub having an inner ring which is connected or connectable to a drive shaft, and having, for the purpose of torque transmission, connection surfaces along an outer periphery of the hub which are connected to the inner ring and to the crown ring. The hub has through-passages between the inner ring and the outer periphery. At least one element, arranged rotationally fixedly on the axial fan wheel inside the crown ring, is designed to maintain a pressure difference in the axial direction when the axial fan wheel rotates.

Abstract: A connecting joint for attaching a wind turbine rotor blade to a rotor hub includes a bolt having a blade end configured to be coupled to the rotor blade and a hub end configured to be coupled to the rotor hub. The bolt includes a neck region adjacent the blade end, wherein the neck region has a cross dimension less than a cross dimension of the blade end of the bolt. A wind turbine blade having such a connecting joint is also disclosed. Additionally, a method of making the connecting joint is disclosed.

Abstract: Aerofoil including: a body comprising first body portion and second body portion bonded to first body portion, first and second body portions having outer faces forming an outer surface of the aerofoil, and inner faces opposing the outer faces; a channel formed within the aerofoil by the inner faces of the first body portion and the second body portion; and a dividing sheet provided within the channel, such that a cooling passage is formed between the dividing sheet and the inner face of at least one of the first body portion and second body portion, cooling passage arranged to conduct cooling fluid adjacent the body, for cooling the body; wherein the body has a rear face and an opposing front face; and the dividing sheet extends parallel to at least a portion of a rear face of the body, such that the cooling passage formed parallel to the rear face.

Abstract: Shroud assemblies and methods for cooling gas turbine engine shrouds are provided. For example, a shroud assembly comprises a shroud segment having hot and cold side portions. The hot side portion faces a gas flow path, and the cold side portion faces a cooling fluid flow path. The shroud assembly further comprises a shroud hanger for mounting the shroud segment in the gas turbine engine. The shroud hanger includes a conduit for receipt of a flow of cooling fluid that defines an outlet configured for the flow of cooling fluid to exit the conduit substantially tangential to the cold side portion of the shroud segment. The shroud and shroud hanger together define an annular cavity that forms the cooling fluid flow path, and fluid exits a plurality of conduits defined in the shroud hanger into the cavity substantially tangential to the shroud cold side to cool the shroud cold side.

Abstract: Provided is an air-sending device in which, in blades, an upstream end of a blade outer periphery is more on an upstream side than an upstream end of a blade inner periphery as seen along a rotation axis, and a downstream end of a blade outer periphery is more on a downstream side than a downstream end of the blade inner periphery, and in which, in the blades, when an angle formed by a line segment, which connects a point internally dividing a line segment connecting the downstream end and the upstream end of an outer periphery of the blades along the rotation axis and a point internally dividing a line segment connecting the downstream end and the upstream end of an inner periphery of the blades along the rotation axis at the same ratio to each other, and a reference line is defined as ?, and a direction inclined toward the downstream side is defined as positive, the angle ? is changed from negative to positive at a duct portion.

Abstract: A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between open and closed positions for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor, at which the inlet-adjustment mechanism is switched from one of its positions to the other. A fixed switch band straddling the threshold line can be used for determining when to initiate the switch of positions so as to time the switch to coincide with the operating point reaching the threshold line. Alternatively, a time to reach the threshold line can be instantaneously computed and compared to the actuator/mechanism response time.

Abstract: An example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.