Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered PA-1 to PA-10, PB-1 to PB-3, HA-1 to HA-9, and SA-1 to SA-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

Abstract: As a precipitate hardening stainless steel has excellent structure stability, strength, toughness, and corrosion resistance, requires no sub-zero treating and is excellent in terms of productivity, a long blade for a steam turbine uses the same. The following are provided: a precipitate hardening stainless steel, which comprises C at 0.05 mass % or less, N at 0.05 mass % or less, Cr at 10.0 mass % to 14.0 mass %, Ni at 8.5 mass % to 11.5 mass %, Mo at 0.5 mass % to 3.0 mass %, Ti at 1.5 mass % to 2.0 mass %, Al at 0.25 mass % to 1.00 mass %, Si at 0.5 mass % or less, and Mn at 1.0 mass % or less, and the balance is composed of Fe and inevitable impurities. The long blade for a steam turbine is composed of this precipitate hardening stainless steel.

Abstract: The invention relates to a housing system (10) for an axial turbomachine, in particular for an aircraft turbine, comprising a housing (12), at least one guide blade (14), which is fastened to the housing (12) by means of at least one fastening element (18),a scaling element (20) for reducing a leakage flow between the listening element (18) and the housing (12), wherein the sealing element (20) is arranged between a downstream wall (22) of the fastening element (18) with respect to a flow direction (I) of the axial turbomachine and a wall (24) of the housing (12), and a pressing means (36), by means of which an axial force can be applied to the scaling element (20) And the scaling element can be pressed against the wall (24) of the housing (12), at least during the operation of the axial turbomachine. The invention further relates to an axial turbomachine having such a housing system (10).

Abstract: A rotor blade (1) provided with an outer covering (2) and with at least one load take-up spar (10) associated with at least one pin-receiving bushing (3). Each spar (10) is a compartmentalized spar comprising centrifugal force take-up means (20) incorporated within a twisting stress take-up casing (30), said centrifugal force take-up means (20) comprising at least two boxes (21, 22), each having said pin-receiving bushing (3) of the spar (10) passing therethrough, each box (21, 22) including a closed retention belt (23) extending in the spanwise direction of the blade, the retention belt (23) of one box (22) surrounding the retention belt (23) of another box (21), each retention belt (23) being provided with unidirectional fibers (24) wound around said pin-receiving bushing (3), said casing (30) being provided with inclined fibers (31) presenting an angle relative to said unidirectional fibers (24).

Abstract: A mechanical coolant pump for an internal combustion engine includes a pump rotor wheel comprising a blocking ring and rotor blades. The rotor blades are configured to pump a coolant radially outwardly. Variable pump stator blades are pivotably supported by a static blade holding ring at a first axial blade end. The variable pump stator blades are arranged radially outwardly of the pump rotor wheel. The blocking ring is arranged to partially overlap a second axial blade end.

Abstract: In general terms, embodiments of the present invention relate to fan assemblies and methods for installing the same. For example, some embodiments of the present invention include a fan assembly that includes: (a) a rotational member; (b) a connection member structured for connection to the rotational member and including a body portion and a head portion; and (c) a blade arm defining an opening therein, such that the opening includes an open end portion and a closed end portion. In some embodiments, the connection member and the blade arm are configured such that, (a) when the blade arm is positioned in a support state, the head portion of the connection member rests against the blade arm to support the blade arm relative to the rotational member, and (b) when the blade arm is positioned in a secure state, the head portion of the connection member at least partially bears against the blade arm adjacent to the opening defined in the blade arm.

Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Abstract: Apparatus, systems and methods of 50 CFM exhaust and ventilation fans for bathrooms with grill covers having removable light lens covers, and flaps/ears that allow the housings to mount directly to joists and/or other structural members inside of a ceiling or inside of a wall. The housing can include a mounting plate having a motor with attached impeller thereon, wherein the mounting plate with motor and attached impeller and electrical connectors can be removed as a single unit from the housing for accessing and inspecting interior wire connections during inspection and for ease in replacing parts such as burned out motors overtime.

Abstract: Various embodiments include an alignment pin for a turbomachine. In some embodiments, the alignment pin includes a hollowed head section for engaging a diaphragm slot in the turbomachine. In these embodiments, the alignment pin further includes an expandable sleeve section connected with the hollowed head, the expandable sleeve section for engaging a casing slot in the turbomachine.

Abstract: The disclosed fluid elements include radial blades extending to trailing edges and that are integral with front and rear shrouds to provide a fluid exit. Fillets adjoin the trailing edge and the front and rear shrouds at the exit. The front and rear shrouds respectively have first and second perimeter thicknesses at the impeller outer perimeter. The first perimeter thickness is greater than the second perimeter thickness at the trailing edge and adjacent to the exit, which provides greater high cycle fatigue in the area of the fillets.

Abstract: A system for securing first and second tubular coaxial components carrying a roller bearing is provided. The system includes a forcing nut mounted inside the coaxial components and axially abutting against the first component after screwing-in of the second component; and a locking pin for preventing unscrewing of the nut and being arranged between the nut and the first component. The system also includes a cylindrical sleeve being arranged between the pin and the first component, being secured axially relative to the first component, and including an axial stop against which the pin is applied; and first and second devices for linking the pin and the first component in rotation, respectively, with the sleeve.

Abstract: A system includes a solid feed pump. The solid feed pump includes a housing, a rotor disposed in the housing, a curved passage disposed between the rotor and the housing, a solid feed inlet coupled to the curved passage, a solid feed outlet coupled to the curved passage, and a rotatable sleeve configured to rotate to actively draw solid feed into the solid feed inlet or out of the solid feed outlet.

Abstract: The present invention relates to a gas-turbine balancing device with at least one annular groove provided on the outer circumference of at least one intermediate or high-pressure rotor of an intermediate or high-pressure compressor, with at least one balancing element being arranged in the annular groove, and with the balancing element being moveable in the circumferential direction along the annular groove and provided with a fixing device.

Abstract: A cooling channel (36, 36B, 63-66) cools inner surfaces (48, 50) of exterior walls (41, 43) of a component (20, 60). Interior side surfaces (52, 54) of the channel converge to a waist (W2), forming an hourglass shaped transverse profile (46). The inner surfaces (48, 50) may have fins (44) aligned with the coolant flow (22). The fins may have a transverse profile (56A, 56B) highest at mid-width of the inner surfaces (48, 50). Turbulators (92) may be provided on the side surfaces (52, 54) of the channel, and may urge the coolant flow toward the inner surfaces (48, 50). Each turbulator (92) may have a peak (97) that defines the waist of the cooling channel. Each turbulator may have a convex upstream side (93). These elements increase coolant flow in the corners (C) of the channel to more uniformly and efficiently cool the exterior walls (41, 43).

Abstract: This is a system and apparatus for precisely mounting a ring shroud to a motor vehicle cooling system and engine. A cooling fan subassembly is mounted to an engine and ring shroud subassembly containing fan braces that are mounted to the engine via mounting brackets. A mounting gap tool is inserted through apertures in the ring shroud to prescribe the radial and axial clearance between the ring shroud and the cooling fan subassembly. Once the ring shroud and cooling fan assembly are aligned to predetermined specifications for clearance, the installer secures all the fasteners in the mounting brackets and retrieves any or all the mounting gap tools.

Abstract: A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

Abstract: An improved wind energy machine for capturing the wind to produce useful work, such as generating electricity. The wind energy machine has a rotating center hub with a center drive shaft and a vertical axis disposed therethrough. An output shaft is attached to or integral with the drive shaft. Extending outward from the center hub are a plurality of arms that each have an arm support structure comprising a plurality of frame members. The arms rotate the center hub and drive shaft. Pivotally attached to each arm support structure is at least one sail structure that supports a sail. The sail structures pivot to close the sails and engage the wind on one side of the machine and open to allow the wind to pass through on the opposite side. In a preferred embodiment, a pivoting kicker sail provides additional rotation action and a shroud structure helps trap the wind.

Abstract: A balanced rotor component for a gas turbine engine having a aerofoil with a root and an rotor with an axial aerofoil root slot. The aerofoil root has a cavity which holds a balance weight. The cavity is open along at least one wall and the balance weight is spaced from the slot wall to minimise stress concentrations.

Abstract: A rope-conveyor structure for supporting plates of a wind or water power generator, in which plates are coupled to a rope at positions spaced apart from each other so that the force of flowing water or wind applied to the plates rotates the rope. The rope-conveyor structure includes couplings which are coupled to the rope between the plates, and connection wires each of which has a predetermined length. Each connection wire is connected at a first end thereof to the corresponding coupling and at a second end thereof to the corresponding plate. The positions of the connection wires can be selectively changed so that each connection wire can support the corresponding plate in either directions. Therefore, the plates can be prevented from being displaced from the correct positions or from twisting, regardless of the direction of flow of the water.

Abstract: A disclosed centrifugal boost pump volute includes normal to flow cross sectional surfaces distributed over the length of the passage. The volute includes a volute proper, an exit bend and a diffuser fluidly interconnecting the volute proper to the exit bend. The cross sectional surfaces are defined as dimensions set out in one set of data, which includes Tables N-1 and N-2 for the volute proper and Table N-3 for the volute exit bend, where N is the same value.