A centrifugal pump with a rotor having at least one blade and a method for configuring the profile of a blade is provided. The blade has a profile which is obtained by superposing a symmetric profile with at least one additional profile and a camber line whose blade inlet angle is smaller than 0.

An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.

In some embodiments, a plenum of an apparatus for transferring energy between a rotating element and a fluid may include a through hole disposed through the plenum; a plurality of inlet guide vanes disposed proximate a peripheral edge of the through hole, the plurality of inlet guide vanes comprising a first group of inlet guide vanes having a symmetrical profile, a second group of inlet guide vanes, and a third group of inlet guide vanes, wherein each inlet guide vane of the second group and third group have a cambered profile, and wherein each inlet guide vane of the third group has a different cambered profile from each other inlet guide vane of the third group.

A fuel distribution device is provided wherein an axis is defined. The device comprises a body housing a distribution path for fuel; the distribution path has one inlet and a plurality of outlets; the inlet is located on the external surface of the body at an end of an inlet branch of the distribution path; the plurality of outlets are located on the external surface of the body at ends of a corresponding plurality of outlet branches of the distribution path; the inlet branch and the outlet branches are fluidly connected to a distribution space; and the outlet branches are arranged radially.

In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.

An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.

A gas turbine engine comprises a nacelle and a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle has inner periphery that is substantially axially symmetric about a center axis of the rotor from either a throat of the nacelle at a substantially bottom dead center location, or a point of inflection at which the inner periphery of the nacelle at substantially bottom dead center merges a convex portion into a concave portion.

The invention relates to a rotationally symmetrical part, such as a disk (24), for a turbine engine rotor. Said part has a rotational axis (A) and comprises, on the periphery thereof, an annular row of teeth (22), said teeth defining grooves (34, 34) therebetween for therein holding fir tree-shaped rotor blade roots (10, 10). Each tooth comprises a first side flank (40), comprising at least two projecting portions that are intended for holding a blade root and are separate from each other by a hollow portion, and a second side flank (40) comprising at least two projecting portions (42) that are intended for holding an adjacent blade root and are separated from each other by a hollow portion. Said at least two projecting portions of the first flank are located on circumferences (C3, C7) centered on the rotational axis of the rotationally symmetrical part, and said at least two projecting portions of the second flank are located on circumferences (C4, C8) centered on said rotational axis. Said part is characterized in that each tooth has, on substantially the entire longitudinal dimension thereof, a lack of symmetry in relation to a substantially radial median longitudinal plane (P2). At least one (C4) of said circumferences of the projecting portions of the second flank of each tooth is located between the circumferences (C3, C7) of the projecting portions of the first flank and is radially shifted from said circumferences.

Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.

A fairing installed in a bypass duct defined between an outer casing and an inner casing around an axis of a turbofan engine to make compressed air bypass a low pressure compressor is comprised of a fore section elongated aftward from the inner casing at an inlet of the bypass duct and running along an internal periphery of the outer casing; and an aft section elongated aftward in succession to the fore section and curved in a direction getting away from the internal periphery so as to increase an area of a flow path toward an aft end of the aft section, the whole of the aft section being curved.