Abstract: A method of making a wind turbine blade, and the turbine blade resulting form the process, is described in which correct alignment of the shear webs (42a, 42b) upon mould (30) closing is ensured. The method involves providing a first half shell (32a) and a second half shell (32b) to be joined together to form the wind turbine blade. A first edge (46) of a shear web (42) is attached to an inner surface (36a) of the first half shell (32a). A shear web mounting region is defined on an inner surface (36b) of the second half shell (32b). At least one guide block (60a, 60b) is attached to the inner surface (36b) of the second half shell (32b) adjacent to the shear web (42) mounting region. The guide block (60a, 60b) has a guide surface (70) oriented transversely to the inner surface of the second half shell (36b).

Abstract: A propulsion unit for an aircraft is provided. The propulsion unit includes a stationary unit having at least one cowl pivotally mounted on an axis collinear with a longitudinal axis of the propulsion unit between an operating position or a maintenance position allowing access to the turbojet engine for regular maintenance operations and irregular maintenance operations. The maintenance position for irregular maintenance operations includes an opening angle of the cowl that is greater than the opening angle of the cowl to carry out regular maintenance operations. The propulsion unit further includes at least one cylinder and at least one safety connecting rod secured to the cowl and stationary unit.

Abstract: There is disclosed a variable vane actuation arrangement 100, 200 comprising a crankshaft 48, 148 comprising a crank web 50,150 and a unison ring assembly 45 comprising a unison ring 34 moveable to vary the pitch of a plurality of variable vanes 26. A connector 42 is fixed with respect to the unison ring 34. The crank web 50, 150 and the connector 42 cooperate by a pin 56—slot 52, 152 mechanism configured so that rotation of the crankshaft 48, 148 causes rotation of the unison ring 34. There is further disclosed a gas turbine engine with a variable vane actuation arrangement.

Abstract: A power transmission system having at least one inlet speed-reducing gear and a main speed-reducing gear, each inlet speed-reducing gear comprising an inlet pinion meshing with an inlet gearwheel. The inlet gearwheel is constrained to rotate with a main pinion of the main speed-reducing gear, the main pinion meshing with a main gearwheel. At least one inlet gearwheel is secured to reversible connection means in order to be capable of driving a first additional drivetrain connected to an additional rotor.

Abstract: A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment (31) suitable for forming at least a portion of a blade root, a second longitudinal segment (32) extending the first longitudinal segment (31) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment (33) extending the second longitudinal segment (32) upwards, and suitable for forming an airfoil portion, a first transverse segment (34) extending transversely from the junction between the second and third longitudinal segments (32, 33), and suitable for forming a first platform, and a first oblique segment (36) extending from the junction between the first and second longitudinal segments (31, 32) to the first transverse segment (34), and suitable for forming a retaining leg (26) for the first platform.

Abstract: A spar for an airfoil comprises a core, e.g. a foam core, a central structural member extending through the core, an outer structural layer surrounding the core and central structural member and a plurality of yarns extending through the central structural member.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. A first endwall piece includes a first cup portion that defines a first cavity. A second endwall piece includes a second cup portion that defines a second cavity and an airfoil wall portion that projects from the second cup portion. The airfoil wall portion forms a portion of the airfoil profile of the airfoil section. An airfoil piece defines another portion of the airfoil profile. The airfoil piece has first and second ends. The first end is disposed in the first cavity and the second end is disposed in the second cavity such that the airfoil piece is trapped between the first endwall piece and the second endwall piece.

Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.

Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.

Abstract: A retaining structure-based heat transfer and dissipation system and a wind generator set are provided. The heat transfer and dissipation system includes a envelop enclosure and power transmission cables that are laid along the vertical direction of the inner wall of the envelop enclosure. The power transmission cables are laid in a shady surface region of the envelop enclosure. The system effectively lowers the surface temperature of the power transmission cables in the envelop enclosure, prolongs the service life of the power transmission cables, and ensures the operation safety of power transmission. The over-temperature problem of the power transmission cables in a tower drum of the wind generator set in a high-temperature natural geographical environment is resolved in a “green” and “zero-energy consumption” manner, and the system safety of power transmission is improved.

Abstract: A method of manufacturing a composite material vane with a covering element, the vane including a platform and a profile extending perpendicularly to the platform, comprises the following steps: providing a covering element and a preform of the vane, the preform comprising a platform portion and a profile portion extending substantially perpendicularly to the platform portion; positioning the covering element against the platform portion so as to obtain an assembly; placing said assembly in a mold; injecting a first resin into the mold so that said resin impregnates and covers the preform and covers at least a portion of the covering element; and carrying out a heat treatment so as to harden the first resin.

Abstract: The present invention flow rollers are a moving surface boundary layer control method that can reduce surface friction in, automobiles, aircrafts, ships, high speed trains, launch vehicles, sound barriers, temperature barriers, and housings. In a moving surface airflow control system, a flow roller device for mounting on a vehicle for reducing fluid resistance has a first elongated rotating body mounted on a first axis of rotation. The first axis of rotation defines a first forward portion and a first rear portion. The first forward portion is in front of the first axis of rotation, and the first rear portion is behind the first axis of rotation. The first forward portion is configured to move with the fluid flow in a direction along a longitudinal midline and rotate with the airflow.

Abstract: An axial fan includes a motor, an impeller and a hub of the impeller for connecting to a shaft of the motor. A bottom wall of the hub has a central portion and an outer annular portion connected to the central portion by an intermediate portion defined by a plurality of blades arranged radially and angularly distributed about an axis of rotation. The blades are elasto-plastic blades and are able to prevent the impeller from moving axially parallel to the axis, moving radially perpendicular to the axis and a bending of the impeller with movements normal to the plane in which the mean surface of the impeller itself lies. The blades allow a movement with torsional bending around the axis to allow the damping of the resonance frequencies of the assembly formed by the impeller-shaft-rotor.

Abstract: A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity.

Abstract: A blower, including: a volute including air inlets and an air outlet; a wind wheel disposed in the volute; and air collectors. Each air collector includes a curved air guide. The air inlets are disposed at two sides of the wind wheel, respectively. The air collectors correspond to the air inlets. The curved air guide extends into the volute, and the inner diameter of the curved air guide decreases stepwise. The relationship between a minimum inner diameter D0 of the curved air guide and an inner diameter D1, an outer diameter D2 of the wind wheel fulfills the following formula: D1+?(D2?D1)?D0?D1+?(D2?D1). An exhaust fan that includes the blower is also provided.

Abstract: This disclosure relates to a control system and method for the centrifugal compressor. The system, for example, includes a controller configured command an adjustment of at least one of (1) a flow regulator and (2) a speed of a shaft in order to provide safe, efficient compressor operation. Centrifugal compressors are used to circulate refrigerant in a chiller via a refrigerant loop. Centrifugal compressors operate efficiently before reaching a condition known as surge.

Abstract: Bayonet connection key includes upper and lower blocks shaped to be inserted one at a time into a key space, having laterally spaced apart upper and lower flat first and second side contact surfaces, and means for retaining blocks against each other. Bolt or screw may be disposed through an aperture in retaining plate and screwed into threaded hole in upper block pressing retaining plate against lower block. Upper block may include axially spaced apart upwardly extending forward and aft lugs, aft lug shorter than forward lug, and inwardly extending upper stop lug at aft end of upper block. Alternatively bendable tab extending axially forward from a front end of the lower block may be bent up contacting upper block for retaining blocks in key space. Upper block may include forward and aft lugs of same radial length and inwardly extending stop lug at aft end of lower block.

Abstract: The present application provides a turbine bucket. The turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a cooling circuit extending within the platform and the airfoil. The cooling circuit may include a root turn with an asymmetric shape so as to reduce stress concentrations therein.