Abstract: The present disclosure relates generally to a variable area turbine vane row assembly. In an embodiment, the variable area turbine vane row assembly includes rotatable vanes that are circumferentially biased and/or axially biased with respect to adjacent fixed vanes. In another embodiment, the variable area turbine vane row assembly includes multiple rotatable vanes positioned between adjacent fixed vanes, which may optionally be circumferentially biased and/or axially biased with respect to each other as well as to the adjacent fixed vanes.

Abstract: A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet.

Abstract: A locking spacer, which is fitted in a dovetail slot provided on an outer circumferential surface of a disk put on a rotor shaft, includes: a pair of first blocks each provided with a dovetail joint and a stepped seating surface with a first bolt hole, and configured to have a size occupying a portion of an internal space of the dovetail slot; a second block having a size to be inserted into a remaining portion of the internal space of the dovetail slot, and having a height corresponding to the seating surfaces; a fixing plate seated on both the seating surfaces of the first blocks and an upper surface of the second block, and provided with second bolt holes corresponding to the first bolt holes; and a bolt screwed into the first bolt hole through an associated second bolt hole.

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: A compressor blade locking device can include: a first support including a first locking groove; a second support including a left groove and a first protrusion corresponding to the first locking groove; a third support including a second locking groove; a fourth support including a right groove and a second protrusion corresponding to the second locking groove; a center support disposed between the second support and the fourth support; and a tab disposed in the center support, wherein the tab is configured to be turned such that the tab is disposed in the left groove and the right groove.

Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.

Abstract: A fuel pump includes a cartridge removably received within a canister. The cartridge includes a motor assembly, and a pump assembly that includes a centrifugal pumping element and outlet porting from the centrifugal pumping element. The motor drives the centrifugal pumping element to generate a flow of fluid through a main flow pathway between a pump inlet and outlet through the outlet porting of the pump assembly. The cartridge further includes a pressure relief valve that is movable between a closed position and an open position, and defines a pressure relief flow pathway integrally within the cartridge from the outlet porting to inlet porting of the centrifugal pumping element. When pressure within the pump assembly exceeds a threshold pressure, the pressure relief valve moves from the closed position to the open position to permit a relief flow of fluid through the relief flow pathway. The fuel pump may be employed as part of an aircraft fuel system.

Abstract: A wind turbine blade is reinforced while suppressing possible stress concentration resulting from a load imposed on a blade root portion of the wind turbine blade in a flap direction. The wind turbine blade includes a blade main body extending from the blade root portion toward a blade tip portion and an FRP reinforcing layer formed so as to cover at least a part of the outer surface of the blade root portion of the blade main body. The FRP reinforcing layer includes a plurality of laminated fiber layers and a resin with which the plurality of fiber layers is impregnated. The FRP reinforcing layer is formed such that, in a cross section along a longitudinal direction of the blade main body, both ends of the plurality of laminated fiber layers in the longitudinal direction are tapered.

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: A coolant pump for an internal combustion engine includes a delivery duct, a drive shaft, a coolant pump impeller arranged on the drive shaft to covey a coolant into the delivery duct, a control slide which controls a cross-section of an annular gap arranged between an outlet of the coolant pump impeller and the delivery duct, a side channel pump with a side channel pump impeller arranged on the drive shaft and a side channel, a pressure duct comprising a cross-section which fluidically connects an outlet of the side channel to a first pressure chamber of the control slide, a valve which opens and closes the cross-section of the pressure duct, and a first housing part arranged to have the side channel be formed therein and the control slide slidingly guided thereon. The coolant pump impeller is integrally formed with the side channel pump impeller.

Abstract: An anti-icing wind power blade, consisted of a wind turbine blade, wherein the wind turbine blade is provided with an anti-icing heating device, and wherein the anti-icing heating device consists of an air heating system and an electric heating system, wherein the two systems are independent from each other, without mutual interference, and heat the wind turbine blade separately or simultaneously.

Abstract: Wind turbine blade having at least one longitudinal hollow element that defines an aerodynamic outer surface and an inner cavity having an inner surface. The blade also comprises at least one spar (1), disposed in the inner cavity and bonded to the inner surface by at least two bonding surfaces (13) located on bonding surfaces (2) of the spar (1). The spar (1) comprises, on at least one bonding zone (2), at least three fibre fabric layers (3) and at least one central core (4) and at least one lateral core (5) disposed between the at least three fibre fabric layers (3). This makes it possible to increase the resistance to shear stresses in the adhesive bond of the spar (1) to the inner surface of the longitudinal hollow element and decrease the required amount of adhesive.

Abstract: A supercharging device (20), having: a housing (21) which has a longitudinal axis (L); at least one housing inlet (1) which leads into the housing (21); at least one housing outlet (2) which leads out of the housing (21); at least one compressor wheel (5) which is arranged in a compressor chamber (15) and which is driven by a motor shaft (16) and which is arranged between the housing inlet (1) and the housing outlet (2) of the housing (21) as viewed in the flow direction, and at least one bypass duct (17) which is integrated in the housing (21) and which connects the housing inlet (1) to the housing outlet (2) so as to bypass the compressor chamber (15). The bypass duct (17) has a self-adjusting valve (22). The housing inlet (1) and the housing outlet (2) are formed as an axial inlet and an axial outlet respectively.

Abstract: An impeller includes a back cover plate, and vanes and a hub disposed on the back cover plate. The impeller further includes a sealing ring disposed on one end of the impeller away from the back cover plate. A pump using the impeller includes a volute housing and a driving device. The volute housing includes a diffusor chamber, an inlet pipe and an outlet pipe. The impeller is rotatably received in the diffusor chamber and connected to the driving device. A baffle portion is disposed on an end wall in the diffusor chamber adjacent the inlet pipe. The baffle portion engages with the sealing ring to prevent back flow of the fluid. The pump has enhanced fluid delivery efficiency. The back cover plate may further define arc strip-shaped balance holes for reducing an axial force applied to the impeller, such that rotation of the impeller is more stable.

Abstract: A blade pitch adjustment system comprising a yoke arranged to be moved in a first direction in response to an actuator; a plurality of trunnion pins arranged to be attached to a respective propeller blade; a respective contact surface between the yoke and each trunnion pin such that movement of the yoke causes rotation of the blades, and wherein the contact surfaces differ so as to create different angles of rotation of the blades at different points of yoke movement or actuator stroke.

Abstract: A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a downstream cover plate and a downstream angel wing that extends axially from the downstream cover plate. A portion of the downstream cover plate radially outward of the downstream angel wing defines an approximately linear profile. The turbine blade also includes a dovetail region that extends radially inwardly from the shank. A profile of a portion of the downstream cover plate radially inward of the downstream angel wing is recessed relative to the linear profile.

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.

Abstract: The invention relates to a turbine for generating work by a stagewise expansion of a gas, such as steam wherein a downstream stage guide average height is less than an adjacent upstream stage runner average height.

Abstract: A combustor assembly for a gas turbine engine includes a TOBI module which includes a TOBI housing. The TOBI housing has a slot. A vane including a dovetail is removably received within the slot.

Abstract: A modular assembly for a turbine engine has an annular bearing support that is configured to be connected to a first anti-friction bearing, which is configured to be fitted around a first shaft of the turbine engine. The modular assembly further includes a second anti-friction bearing configured to be fitted around a second shaft of the turbine engine, wherein the second shaft is not parallel to said first shaft.