A component stage for a turbomachine includes a component section. The component section includes a flowpath surface at least partially exposed to a core air flowpath defined by the turbomachine, when the component stage is installed in the turbomachine. The component further includes a plurality of sequentially arranged riblets on the flowpath surface, the plurality of sequentially arranged riblets customized for an anticipated location of the flowpath surface within the turbomachine by defining one or both of a non-uniform geometry or a non-uniform spacing.

A planetary gear system for a gas turbine engine with a plurality of planetary gears coupled to a carrier device, with front planetary gears mounted on pins in a front row and aft planetary gears mounted on pins in an aft row, the two rows being parallel to each other in the axial direction of the planetary gear system. The carrier device includes a base structure being in one piece with the carrier device, the base structure positioned around a rotational axis of the gas turbine engine. The pins are coupled to the carrier device through first and second extension elements for the positioning of the pins relative to the base structure. The second extension elements axially extending the respective pins further away from the base structure than the pins positioned by the first extension elements.

The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (1-3) connected to one another in the circumferential direction (U), wherein shells adjacent in the axial direction have cross sections opened counter to a throughflow direction (A) and/or a thread axis inclined counter to the throughflow direction.

A compressor wheel of a charging device may include a hub, a plurality of blades and a wheel back. The wheel back may have an undulating profile which extends from the hub in a radial direction. The undulating profile may include a plurality of regions. The plurality of regions may adjoin one another and may include a first concave region, a second convex region, a third concave region, and a fourth convex region. The second convex region may adjoin the first concave region. The third concave region may adjoin the second convex region. The fourth convex region may adjoin the third concave region.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) also has an at least partially wavy inflow edge (4), that forms a wave (W) having a specific three-dimensional waveform.

An exhaust mixer arrangement for a gas turbine engine comprises an exhaust cone, a lobed exhaust mixer surrounding at least a portion of the exhaust cone and a cover mounted to an outer surface of the exhaust cone. The cover and the outer surface of the exhaust cone define a dead-end cavity for receiving a stiffener ring. A plurality of circumferentially spaced-apart struts interconnect at least a number of lobes of the lobed exhaust mixer to the stiffener ring.

A stator designed to be placed radially in a flow which passes through one or more rotors which share the same axis of rotation, with a leading edge and a trailing edge. The leading edge and trailing edge are connected by a lower face and an upper face, wherein at least one of the faces of the stator has radial undulations which extend axially from the leading edge to the trailing edge. The radial undulations can have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimeter on at least part of the axial length of the stator. A propulsion assembly formed by the rotor and the stator, and to a turbine engine comprising such assembly is also provided.

A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 m and a depth of 25-50 m.

A carrier segment for forming a carrier section for one or more gas turbine engine components, the carrier segment including a carrier wall extending between front and rear carrier ends and having a circumferential profile, the carrier segment being configured for defining radially inwardly thereof a chamber for receiving cooling air from an outboard feed source via the front end, wherein the circumferential profile of the carrier wall is undulating, e.g. with a simple waveform configuration or a more complex arrangement of interleaved series of oppositely oriented part-conical surface formations.

A cover band assembly of a blade row of stator or rotor blades is provided. The cover band assembly comprises a blade row that is arranged inside a main flow path of a continuous-flow machine and has multiple blades which respectively have a front edge and a rear edge; and a cover band of the blade row that is at least partially embedded in a component or a component group as regarded in a longitudinal section of the continuous-flow machine, wherein a cavity is formed that surrounds the cover band and is connected to the main flow path by way of two cavity openings, wherein the front cavity opening is provided upstream of the front edge and the rear cavity opening is provided downstream of the rear edge of the blades of the blade row. Here, the cover band has a leading edge and a trailing edge.