A radial impeller includes a hub, a disk, and a plurality of blades. The disk is affixed to the hub. The disk has a disk plane defined by the disk. Each blade of the plurality of blades is affixed to the disk. Each blade includes a C shaped body portion and an upper and lower horizontal extension. The upper horizontal extension extends along an upper plane parallel to the disk plane. The lower horizontal extension extends along a lower plane parallel to the disk plane.

A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades are coupled with the disk for rotation therewith. The platform system includes a plurality of platforms arranged around the blades and a coverplate that blocks movement of the platforms relative to the disk.

A flight vehicle has a propulsion system that includes an air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes an obstruction that protrudes inwardly from an inner wall of the isolator, into the flow channel in which air flows through the isolator. The obstruction diverts the flow to either side of it. Downstream of the obstruction the flow on either side of the obstruction comes together again, leading to mixing of the flow, for example including mixing of low energy and boundary layer flow with high energy flow. This mixing of flow may make for a more uniform flow at the exit of the isolator. In addition the obstruction may help fix the location of shocks within the isolator, providing longer flow mixing length in the isolator.

A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.

A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.

A housing element (12) for an intermediate turbine housing of a gas turbine, in particular an aircraft gas turbine; the housing element (12) being installable or installed in the intermediate turbine housing radially outwardly, in each case between a plurality of circumferentially spaced struts; the housing element (12) having a planar form and, relative to the radial outer side (16) thereof, a plurality of depressions (18c), is provided. On the radial inner side (32, 34) thereof, the housing element (12) has at least one recess (26) that is configured outside of the regions in which depressions (18c) are formed on the radial outer side (16).

A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

A rotationally symmetrical part, such as a disk, for a turbine engine rotor. The part has a rotational axis (A) and includes, an annular row of teeth defining grooves therebetween for therein holding fir tree-shaped rotor blade roots. Each tooth includes a first side flank, having at least two projecting portions for holding a blade root and separated from each other by a hollow portion, and a second side flank including at least two projecting portions for holding an adjacent blade root and separated from each other by a hollow portion. Each tooth has, on substantially the entire longitudinal dimension thereof, a lack of symmetry in relation to a substantially radial median longitudinal plane. At least one of the circumferences of the projecting portions of the second flank is located between the circumferences of the projecting portions of the first flank and is radially shifted from the circumferences.

A tie for a component includes a body including an elongate portion and an arch disposed adjacent to the elongate portion. The arch includes first and second middle surfaces extending between a pair of first and second outer curved surfaces, respectively. The body defines a minimum cross-sectional plane perpendicular to a longitudinal axis and passing through the elongate portion. The body further includes a minimum tie width at the minimum cross-sectional plane along a second transverse axis. The minimum tie width is greater than each of a first minimum arch width of the first middle surface and a second minimum arch width of the second middle surface by a width factor greater than or equal to 3 to less than or equal to 10.

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.