Abstract: A vane for a gas turbine engine includes a radially inner platform and a radially outer platform. At least two airfoils extend between the radially inner platform and the radially outer platform. At least two anti-rotation tabs extend axially from the radially outer platform.

Abstract: A gas turbine engine system includes a drive shaft and a compressor located in a compressor case. The compressor has a number of rotors. Each rotor includes a number of blades radially extending from a rotor wheel and terminating in a blade tip. The blade tip terminates in close proximity to the case and defines a tip clearance. An air flow control system is coupled to the compressor. The air flow system includes inductive coils and plasma actuators coupled to the case and magnets coupled to the blade. The plasma actuators induce air flows in order to, for example, mitigate air flow leakage around the tip of the blade.

Abstract: The present invention relates to a blade folding apparatus that may incorporate an overhead blade lifting system that reduces binding loads on blade pins induced by blade weight and pitch, and a folding mechanism that removes the necessity of personnel with external guide-poles to rotate main rotor blades. The apparatus may include flap locks, an overhead lifting system support structure attached to the flap locks, and two blade support beams to create and support a lifting point near each blade's longitudinal and lateral center of gravity. The blade support beams may be fitted with an articulation mechanism that lifts and/or lowers the overhead lifting structure. The apparatus facilitates rapid folding of the main rotor blades, and, when used with blade clamping mechanisms, is capable of aiding in the removal and/or the re-installation of the main rotor blades without external lifting mechanisms.

Abstract: An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge.

Abstract: Disclosed herein is a plurality of blades with a three-dimensional shape injection-molded at the same time, thereby reducing processes of manufacturing a centrifugal fan assembly. A centrifugal fan assembly includes a blade assembly formed by integrally injection-molding a plurality of blades where at least a part thereof is bent and a fixing portion, and a hub plate to which the fixing portion of the blade assembly is coupled, where the fixing portion includes at least one opening to allow extraction of the blade assembly from the mold.

Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.

Abstract: A turbine blade has a body enclosing a labyrinth of internal channels for circulation of coolant received through an inlet integrally formed in terminal portion of blade root. The labyrinth includes; inlet arranged on an axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section axially downstream of first, second section having reduced cross section compared to first section. Leading edge passage intersects first section and extends through blade body towards the tip. Main blade passage intersects second section. Trailing edge passage intersects downstream duct portion which is in axial alignment with but separate from second section and channel connects second section with the downstream duct portion. Channel has reduced cross section compared to second section and downstream duct portion. The inlet has an inverted keyhole shape with cross section extends through upstream duct portion first section.

Abstract: A stationary blade includes a main unit having a hollow blade structure formed from a metal plate by plastic forming. The stationary blade includes a blade tail section. In a blade tail upper portion, the metal plate has a concave-shaped recess and a rib formed on an inner surface side thereof and the metal plate further has slits formed by slitting on a blade pressure side thereof, so that droplets affixed on a blade surface can be guided into an inside of the hollow blade when the blade tail section is joined to the hollow blade main unit. The recess in the metal plate is covered so as to be lidded by a suction-side protrusion of a suction-side metal plate from a blade suction side to thereby form a hollow blade tail section. The metal plates are welded together to the main unit.

Abstract: A rotor disk blade for a turbine engine, the blade being made of composite material including fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a portion constituting an airfoil and a blade root forming a single piece, the blade root having two substantially plane opposite lateral flanks that are formed respectively extending the pressure side surface and the suction side surface of the airfoil. The blade root is clamped between two metal plates fastened against the lateral flanks of the blade root by a bolt and a nut passing through the plates and the blade root. The bolt has a head bearing against one of the two plates. The nut has a head bearing against the other plate.

Abstract: A fan disk is for a jet engine in which there flows a gas stream in a flow direction. A pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.

Abstract: A rotor blade for a wind turbine, having a longitudinal rotor blade base body extending in a longitudinal axis, with the rotor blade base body defining a leading edge and a trailing edge of the rotor blade is provided, wherein the rotor blade base body has a number of panel elements, wherein at least one panel element includes at least one stiffening structure member embedded within the at least one panel element.

Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.

Abstract: The present disclosure is directed to pre-cured composites for use in manufacturing rotor blade components of a wind turbine. In one embodiment, the pre-cured composites are pultruded composites having a continuous base portion with a plurality of integral protrusions extending from the continuous base portion, and a fabric layer cured with the continuous base portion. Further, adjacent protrusions are separated by a gap.

Abstract: A center body support for a gas turbine engine includes an outer annular wall. An aft flange extends radially outward from the outer annular wall. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange, brace and forward portion of the outer annual wall provide a unitary, one-piece structure.

Abstract: A gas turbine engine including a rotor and a cooling fluid delivery system is presented. The rotor includes a disc and a plurality of blades extending radially therefrom. Each blade has a suction side and a pressure side and includes a shank, a platform and a main portion, the main portion being radially outward of the shank and separated therefrom by the platform. At least one cavity is defined, each radially inward of the platforms and between a suction side of the shank of one blade and a pressure side of the shank of an adjacent blade. The rotor includes at least one damper, the damper including a main body in contact with at least one blade and a deflector nose. The deflector nose extends from the main body into the cavity.

Abstract: Turbine assemblies and related turbocharger systems having direct turbine interfaces are provided. One exemplary turbine assembly includes a first turbine housing having an outlet portion defining a fluid outlet of a first turbine and a second turbine housing having an inlet portion defining a fluid inlet of a second turbine, wherein at least a portion of the inlet portion radially surrounds at least a portion of the outlet portion to provide a direct interface from the fluid outlet of the first turbine to the fluid inlet of the second turbine in an axial direction.

Abstract: Turbine assemblies and related turbocharger systems having direct turbine interfaces are provided. One exemplary turbine assembly includes a first turbine housing having an outlet portion defining a fluid outlet of a first turbine and a second turbine housing having an inlet portion defining a fluid inlet of a second turbine, wherein at least a portion of the outlet portion radially surrounds at least a portion of the inlet portion to provide a direct interface from the fluid outlet of the first turbine to the fluid inlet of the second turbine in an axial direction.

Abstract: A regulator assembly, comprising a vaned diffuser, a motor, a driving gear engaged with a driven gear, the driven gear having rectangle-shaped through holes thereon, the rectangle-shaped through holes disposed and extending along an axis of the driven gear, and a regulating mechanism including a regulator, a supporting member, wherein the regulator is sleeved on the supporting member, and wherein the vaned diffuser is fixed on the supporting member, and regulator sliding members fixed to the regulator through the rectangle-shaped through holes of the driven gear, whereby the motor is configured to drive the driving gear to rotate, the driving gear is configured to drive the driven gear to rotate, the driven gear is configured to push the regulator sliding members to move, and the regulator sliding members are configured to drive the regulator to rotate relative to the vaned diffuser, thus driving the regulator to move along its axis.

Abstract: A composite fiber component for a rotor blade of a wind power plant including a first sandwich core and a second sandwich core arranged next to each other, each having an inside facing a rotor blade interior and an outside facing a rotor blade exterior. A first fiber-containing laminate layer is arranged on the inside of the first sandwich core and on the outside of the second sandwich core. A second fiber-containing laminate layer is arranged on the outside of the first sandwich core and on the outside of the second sandwich core. And, a third fiber-containing laminate layer is arranged on the inside of the first sandwich core and on the inside of the second sandwich core. Also disclosed is a rotor blade for a wind power plant having a composite fiber component as disclosed.

Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge of the platform. A related turbomachine is also disclosed.