A counter-rotating fan, comprising an impeller assembly and an air guide structure. The impeller assembly comprises a first stage impeller and a second stage impeller, of which the rotation directions are opposite. The pressure surfaces of first blades of the first stage impeller are configured to be opposite the suction surfaces of second blades of the second stage impeller, and from the blade root to the blade tip, each of the first blades and the second blades bends toward its own rotation direction. The air guide structure comprises a flow guide cover. The flow guide cover is provided at the center position of the air intake side of the first stage impeller, and the air intake side surface of the flow guide cover at least partially forms a flow guide surface, the flow guide surface extending along the axis of the first stage impeller in the direction away from the counter-rotating fan.

Fairing installations disclosed herein may include a damper for mitigating vibration of a cantilevered fairing disposed in a bypass duct of a gas turbine engine. The bypass duct may include a first shroud radially spaced apart from a second shroud to define a bypass passage between the first and second shrouds. The fairing may be disposed in the bypass passage and cantilevered from the first shroud. The fairing may have a secured end secured to the first shroud and a free end proximate the second shroud. The damper may be engaged with the free end of the fairing to damp movement of the free end of the fairing.

The invention relates to an assembly for a turbomachine extending along an axis (X) and comprising:—a ferrule (32) designed to define a fan duct (5) of a gas stream of the turbomachine,—a fan casing (2) radially surrounding the ferrule (32) and defining with the ferrule (32) the fan duct (5),—a rectifier (6) comprising a plurality of vanes (7) comprising a first vane (7a) and a second vane (7b) adjacent to the first vane (7a), the vanes defining between them a converging flow channel (13) designed to direct and accelerate the stream by means of an inlet section (14a) included in a plane non-perpendicular to the axis of the turbomachine and an outlet section included in a plane (14b) perpendicular to the axis (X) of the turbomachine, the first vane (7a) and the second vane (7b) each having an unducted downstream portion which forms a trailing edge.

This steam turbine blade is provided with: a blade body (61) extending in a radial direction and having an airfoil profile in a cross section perpendicular to the radial direction; and a heater (H) including a heating wire disposed so as to extend along a trailing edge (Er) of the airfoil profile in the blade body (61). This configuration makes it possible to further mitigate an efficiency drop due to moisture attached to the surface of the steam turbine blade (60).

A variable-pitch stator blade includes an airfoil having a central portion with a first chord and a first skeleton line delimited by a leading edge and a trailing edge. An end portion has a second chord and a second skeleton line delimited by the leading edge and a downstream limit. A skeleton angle at a first length I1 of the first chord is defined by a function G1(I1), and the skeleton angle at a second length I2 of the second chord is defined by a function G2(I2). The absolute value of the average increase A2 of G2′(I2) between the leading edge and the downstream limit is greater than the absolute value of the average increase Al of Gl′(I1) between the leading edge and a point P, wherein the first length I1 corresponds to the total length of the second chord.

Disclosed are a compressor, which is a cantilever type that is easy to manufacture and assemble, and is capable of minimizing the vane tip clearance as the elastic member absorbs the impact and is compressed when the vane collides with the shroud segment due to expansion of the vane, and a gas turbine including the same.

An air turbine starter having a housing, a turbine, a drive shaft, and at least one vane. The housing having an inlet, an outlet and a curvilinear flow path extending between the inlet and the outlet. The at last one vane is located within a portion of the curvilinear flow path, and includes an outer wall extending between a root and a tip in a span-wise direction and between a leading edge and a trailing edge in a chord-wise direction. In one aspect, the vane is arranged to define an acute axial angle that is non-constant in the chord-wise or span-wise direction. In another aspect, the vane is arranged to define an acute tangential angle that is non-constant in the chord-wise or span-wise direction.

A turbine stator sector includes a plurality of vanes extending along a radial direction between a first end and a second end and along an axial direction between a leading edge and a trailing edge. The sector further includes an internal shroud linked to the first end of the vanes and an external shroud linked to the second end of the vanes. The sector includes at least one annular portion forming all or part of the internal shroud or of the external shroud. The annular portion includes a first partition present at the junction with the first or the second end of the vanes and a second partition held spaced from the first partition along the radial direction by a three-dimensional structure including a plurality of cutouts.

A gas turbine engine includes a plurality of airfoil vanes situated in a circumferential row about an engine central axis. Each of the plurality of airfoil vanes include a first platform, and a second platform, and an airfoil section therebetween. A face of the first platform includes a trailing edge recess and a leading edge recess. The trailing edge recess and leading edge recesses of adjacent ones of the first platforms together define a slot. A sealing element situated in each slot. The sealing element has a geometry that tracks the geometry of the slot such that the seal is trapped in the slot by a form-fit relationship in circumferential and axial dimensions by a form-fit relationship between the sealing element and the slot. A method of sealing a plurality of airfoil vanes is also disclosed.

A stator vane (3) for a turbine (50c) of a turbomachine (50), the stator vane having a stator vane airfoil (3c), an inner shroud (3a) and an outer shroud (3b), the inner shroud (3a) and the outer shroud (3b) bounding an annular space (2), in which working gas (51) is conveyed during operation, radially with respect to a longitudinal axis (52) of the turbomachine (50), and the stator vane airfoil (3c) having a stator vane airfoil channel (3d) extending through its interior between a radially inner inlet (6) and a radially outer outlet (7). A characteristic features is that the inlet (6) is disposed in such a manner that a gas (8) flowing through the stator vane airfoil channel (3d) during operation is at least partially formed of the working gas (51) conveyed in the annular space (2), and thus the working gas is redistributed from radially inward to radially outward.