An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.

The invention relates to a fan wheel having blades (11) which are distributed over the circumference and are connected to one another in the circumferential direction via at least one ring. The fan wheel consists of at least three integrally formed segments (I to VII). Said segments comprise at least one respective ring portion (1) of at least one ring as well as either a blade (II) or at least a portion of the blades. The segments (I to VII) are joined together to form the fan wheel. The ring portions (1) lie against each other with edges (4, 5) which form the joining areas (15, 16) that are disposed transversely with respect to the circumferential direction of the fan wheel. At least one edge (4) of the ring portion (1) of each segment (I to VII) is provided with at least one projecting form-fitting part (18), and at least one edge (4, 5) of the ring portion (1) of each segment (I to VII) is provided with at least one recess (17) which is at least approximately complementary to the form-fitting part (18).

A seal segment has an arcuate body having: a first end; a second end circumferentially opposite the first end; a first face; a second face axially opposite the first face; an inner diameter (ID) face; and an outer diameter (OD) face. The seal segment is shaped to interfit with a plurality of identical seal segments first end to second end to form a seal surrounding a central longitudinal axis. The first face has: a circumferential channel closer to the ID face than the OD face; and a plurality of channels extending from the circumferential channel to the OD face. The ID face has: a circumferential channel closer to the first face than the second face; and a plurality of channels extending from the circumferential channel to the second face. The ID face circumferential channel has an open end.

A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).

Technologies are generally described for pump devices that include an adaptive cutwater and impeller arrangement. The power end of the pump device can be coupled to a motor to drive an impeller. The primer plate and impeller of the pump device are removable from the pump casing such that the primer plate and impeller can be replaced or modified as desired for different applications. In some examples, the pump casing includes a primer plate that is removable from the pump casing, where the primer plate includes a discharge cutwater tongue that is specifically spaced and sized to service an impeller of a desired design. The discharge cutwater tongue and impellers in the pump device may thus be serviced for replacement parts, as well as to modify the pump device for different fluids of different fluids properties or hydraulic requirements as may be needed in different applications.

According to a process for manufacturing a piece having a relatively big size, in particular a blade for a turbine engine, at least two sectors are manufactured separately from each another, so that each of them comprises: a portion having substantially the same shape and size of a corresponding portion of the piece to be made, at least one coupling surface which is complementary to a corresponding coupling surface of the other sector, and a continuous outer flange at each of said coupling surfaces; the sectors are rested against each other at the coupling surfaces and are then fastened to each other by means of an electron beam welding, carried out under vacuum, so as to weld the outer flanges along the entire outer perimeter of the coupling surfaces, and by means of a subsequent hot isostatic compression; after the fastening, the flanges are removed by means of a material removal machining.

The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane (10), a second turbomachine blade or vane (20) adjacent to it, and at least one tuning element guide housing (30) with at least one cavity, in which at least one tuning element (5) is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess (11), in particular in a frame (12), of the first turbomachine blade or vane (10), where the second turbomachine blade or vane (20) has at least one first rib (21) for securing the tuning element guide housing (30) arranged in the recess (11).

When a combination of a vane type of a stator vane and a vane type of a stator vane for one straightening plate is the same as a combination of a vane type of a stator vane and a vane type of a stator vane for the other straightening plate, positions of the first straightening plate side connection portions and the second straightening plate side connection portions of the one straightening plate and the other straightening plate are the same as each other. When the combinations are different from each other, at least one of the positions of the first straightening plate side connection portions of the one straightening plate and the other straightening plate and the positions of the second straightening plate side connection portions of the one straightening plate and the other straightening plate are different from each other.

An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough.

An airfoil attachment system (10) for a modular turbine vane (12) of a gas turbine engine (14) including an outer attachment system (10) with forward and aft radially extending axial hooks (20, 22) configured to be coupled directly to a vane carrier (24) to increase structural integrity of the modular vane (12) is disclosed. The airfoil attachment system (10) may also include one or more midshroud outer supports (26) positioned between the forward and aft radially extending axial hooks (20, 22) to reduce circumferential rocking movement of the airfoil vane back and forth between the suction and pressure sides (28, 30) of the vane (12). The modular turbine airfoil vane (12) may be positioned between adjacent shrouds (32, 34) forming first and second joints (88, 102). A first sealing system (104) may be placed at the first joint (88), and a second sealing system (110) may be placed at the second joint (102) to limit hot gas ingestion.