A centrifugal pump includes a pump housing having a suspension inlet and a suspension outlet and a flow channel between the inlet and the outlet, a shaft mounted by bearings for rotation about a center axis, an impeller which is rotatable by the shaft, in alignment with the inlet and arranged to be rotated about the axis in the flow channel, and gas collecting openings for gas removal arranged in the flow channel. The inlet end of the flow channel includes a number of static vanes comprising gas collecting openings, the vanes extend radially from an inner wall of the flow channel toward the center of the flow channel and are upstream of the impeller.

A method of producing a gas turbine engine fan blade having a geometric configuration is provided. The method includes: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate; depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion; additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion; and shaping the blade blank into the geometric configuration.

A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.

A shroud of a vane of a turbine is provided. The shroud comprises a shroud main body; and a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein, the shroud edge passage is disposed along the circumference of the shroud main body. The shroud edge comprises a plurality of cooling air inlets configured to introduce a cooling air into the shroud edge passage from outside of the shroud edge, and a plurality of cooling air outlets configured to cause the cooling air to flow out of the shroud edge passage to the outside of the shroud edge. The shroud edge passage is divided into three or more sub-passages by the plurality of cooling air inlets and the plurality of cooling air outlets.

A component (1, 2) for supporting at least one bearing (3) for a turbine engine (10) comprising: two coaxial walls, internal (4) and external (5) walls respectively, defining a gas flow vein (6) between them and interconnected by a row of arms (7); an external ferrule (50) comprising an internal peripheral edge (51) connected to the external wall (5) and an external peripheral edge (52) connected to an external mounting flange (53); an internal ferrule (40) comprising an external peripheral edge (41) connected to the internal wall (4) and an internal peripheral edge (42) comprising an internal mounting flange (43); at least one of the ferrules (4, 5), which at the peripheral edge (41, 51) thereof is connected to the corresponding wall (4, 5), having a general shape which is corrugated about an axis (X-X) of the component (1, 2).

Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.

A cooling tower fan hub having a ring and a disc in which in which hollows and recesses are opened in the ring and/or in the disc in order to decrease fan natural frequencies and avoid excitation by the several kind of loads that affect a fan during operation. The number, size and shape of the hollows can be adjusted to tune the fan natural frequencies around the original value.

A turbine section for a gas turbine engine includes inner and outer diameter ceramic matrix composite (CMC) support rings that define a gaspath there between. Each of the inner and outer diameter CMC support rings are monolithic and continuous. CMC vane arc segments are disposed in the gaspath and supported by the inner and outer diameter CMC support rings. Each of the CMC vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter CMC support rings with the CMC vane arc segments to retain the CMC vane arc segments between the inner and outer diameter CMC support rings.

In a turbine rotor blade assembly 1 of the present invention, each turbine rotor blade 10 includes a platform 11 having a blade root 12 fixed to a turbine disk 30, a profile 13 rising from the platform 11, and a shroud 14 provided at a top end of the profile 13. The shroud 14 of the present invention includes a first contact end part 15 that comes into contact with an adjacent shroud adjacent to one end side in a circumferential direction, a second contact end part 16 that comes into contact with an another adjacent shroud adjacent to the other end side in the circumferential direction, and a main body part disposed between the first and second contact end parts 15 and 16. One or both of the first and second contact end parts 15 and 16 are lower in rigidity than the main body part.

The disclosure relates to a weight-optimized, meridian-accelerated rotor including permanent magnets securely supplied with a required cooling during use. The disclosure further relates to a corresponding electrical machine, in which the problem of demagnetization of existing permanent magnets due to rotor temperatures that are too high is avoided. The rotor or the rotor of an affected electrical machine has an annular structure on the outside radius for receiving the permanent magnets. The rotor also has a conical hub structure on an inside radius and a plurality of at least rib-shaped or blade-shaped structures between the annular structure and the conical hub structure in order to form a mechanical connection of the annular structure and conical hub structure.