Abstract: A set of stationary blades for a steam turbine is provided. At least one of the stationary blades includes a suction side and an opposite pressure side, and a plurality of ejection channels defined in the at least one stationary blade. Each of the plurality of ejection channels extends through an outer surface of the pressure side, and each of the plurality of ejection channels is coupled in flow communication to a blade inlet aperture.

Abstract: A centrifugal compressor to be used in a chiller system includes a casing, an impeller, a motor and a diffuser. The casing has an inlet portion and an outlet portion. The impeller is attached to a shaft rotatable about a rotation axis, and has an impeller shroud which encloses the impeller. The motor rotates the shaft in order to rotate the impeller. The diffuser is disposed in the outlet portion downstream of the impeller. The centrifugal compressor further includes a seal bearing. The seal bearing is attached to the inlet portion to seal the impeller shroud, and rotatably supports the impeller and the shaft.

Abstract: A propulsor for a gas turbine engine may comprise a case including a duct disposed along an axis to define a flow path, a rotor including a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path, and a row of guide vanes situated in the flow path. A first guide vane may comprise a radially inner length (LI), a radially outer length (LO), and a midspan length (LM). The first guide vane may have a first dimensional relationship defined as LO/LM. The first guide vane may have a second dimensional relationship defined as LI/LM. The first dimensional relationship and/or the second dimensional relationship may be greater than 1.05.

Abstract: A centrifugal fan is disclosed. The centrifugal fan includes a housing; and a fan wheel, disposed in the housing, the fan wheel including: a fan hub; a plurality of inner fan blades, each of the inner fan blades includes a first contact surface and a second contact surface, the first contact surfaces are connected to the fan hub respectively; a plurality of connection structures, each of the connections structure includes a first side and a second side; and a plurality of outer fan blades, each of the outer fan blades includes a first end and a second end; wherein the second contact surfaces are connected to the first sides respectively, the first ends are connected to the second sides respectively.

Abstract: The present disclosure is directed to a shear web for a rotor blade of a wind turbine and a method of manufacturing and assembling same. The rotor blade generally includes an upper shell member having an upper spar cap configured on an internal surface thereof and a lower shell member having a lower spar cap configured on an internal surface thereof. Further, the shear web extends between the spar caps along a longitudinal length of the blade. In addition, the shear web includes first and second outer pultruded layers at least partially encompassing a core material, wherein end portions of the first and second outer pultruded layers form compressed flanges at opposing ends of the shear web.

Abstract: A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.

Abstract: An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

Abstract: A component includes an outer wall that includes an exterior surface and an opposite interior surface. The component also includes at least one internal void defined adjacent the interior surface and configured to receive a cooling fluid therein. The component further includes a plurality of openings defined in and extending through the outer wall such that the outer wall defines an edge of each of the plurality of openings. Additionally, the component includes a plurality of separable plugs each positioned in a corresponding opening. Each of the separable plugs is sized to fit within the corresponding opening such that a clearance gap is defined between the separable plug and the edge of the corresponding opening. Each of the separable plugs is coupled to the outer wall by at least one tab that extends across the clearance gap from the each separable plug to the edge of the corresponding opening.

Abstract: The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.

Abstract: Aspects of the disclosure are directed to a sync ring assembly associated with an engine, comprising: a sync ring, and a clevis coupled to the sync ring, where the clevis includes a rib that resists a deflection of the sync ring assembly when the engine is operated, and where the clevis is made of titanium.

Abstract: A propeller assembly that includes a hub having an outer radial surface and a plurality of wedge retaining members removably coupled to the hub. The plurality of wedge retaining members are spaced circumferentially about the outer radial surface such that a dovetail slot is defined between adjacent wedge retaining members. The assembly also includes at least one propeller blade including a root portion having a dovetail profile. The root portion is coupled to the hub and positioned within the dovetail slot. The plurality of wedge retaining members are configured to restrict radial movement of the root portion within the dovetail slot.

Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.

Abstract: A control horn arrangement includes a control horn body with an inboard end and an opposed outboard end. The control horn body defines a torque tube axis which extends between the inboard and outboard end of the control horn body. An inner flange and an outer flange are disposed on the outboard end of the control horn body. The inner flange and the outer flange extend about the torque tube axis and define between one another a receptacle to fix a torque tube to the outboard end of the control horn body.

Abstract: An airfoil adapted for use in a gas turbine engine is disclosed. The airfoil may include components made from ceramic materials. The airfoil may include insulating material to thermally isolate portions of the airfoil.

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.

Abstract: An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion.

Abstract: An axial flow fan according to the present invention includes a plurality of blades, each of the blades including: a leading edge formed in front in a direction of rotation of the axial flow fan; an inner circumferential edge formed at an inner circumference of the blades; and an outer circumferential edge formed at an outer circumference of the blades, the outer circumferential edge configured to be at downstream of a fluid, forced to move by the axial flow fan, than the inner circumferential edge, the blade being reflexed toward upstream of the fluid at a portion adjacent to the outer circumferential edge, and having a local angle-decrease section having a blade inlet angle ? at the leading edge decreasing from neighborhood, the local angle-decrease section being formed at a side of the leading edge and being located closer to the outer circumferential edge than to the inner circumferential edge.

Abstract: Within a compressor case, a plurality of stages of high-pressure compressor stators are disposed alternately with a plurality of stages of high-pressure compressor rotors along an axial direction. Each stage of the high-pressure compressor stators includes a plurality of compressor stator vanes. Each of the compressor stator vanes has, on a camber line, a camber reference point in which (???e)/?k is 50% (?, ?e and ?k represents a metal angle, an exit metal angle and a camber angle, respectively). In a vane-shaped cross-section, a distance from a leading edge to the camber reference point is set to a 26-38% chord.

Abstract: A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.

Abstract: Device for generating energy making use of the current of a river (2), with a self-floating paddlewheel (13) and an electric generator set (17) that is coupled to the paddlewheel (13), whereby the device (1) is provided with an immersed housing (3) with an open bottom (4) in which the paddlewheel (13) is rotatably affixed and whereby there is a unit (10) to control the flow of the river (2) at the level of the paddlewheel (13), whereby the speed of the generator set (17) is kept constant by controlling the water level (9) in the housing (3) by placing its internal space (7) under pressure and/or by controlling the aforementioned unit (10).