Airfoils for gas turbine engines are disclosed herein. The airfoils each include a pressure side and a suction side. Vortex-reduction passageways extend from the pressure side to the suction side.

A synthetic jet for a stationary vane for a turbo-machine is disclosed. The synthetic jet includes a backside cavity and a jet cavity. The jet cavity includes a frontside cavity adjoining the backside cavity and a jet passage extending from a fluid stream interfacing surface of the airfoil towards the frontside cavity. The jet passage is in flow communication with the frontside cavity. The synthetic jet also includes a disk located between the backside cavity and the frontside cavity. The disk includes a cylindrical disk and a coating on each side of the cylindrical disk. The coating is a piezo electric ceramic material.

A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface. Bleed air removed from the annular gas flow passage flows through the bleed holes from the inlet to the outlet ends. The outlet end of each bleed hole is located circumferentially upstream of the inlet end relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor.

A shroud configured to be disposed around an impeller of a centrifugal compressor, the shroud has a wall extending around a central axis of the centrifugal compressor, the wall having an inner face oriented toward a gaspath and an outer face oriented away from the gaspath, a slot extending all around the central axis and from the inner face to the outer face of the wall, bridges secured to the wall, the bridges circumferentially distributed around the central axis and spanning across the slot, the bridges extending from roots to tips, the tips of the bridges circumferentially offset from the roots relative to the central axis.

A diffuser for a compressor of a gas turbine engine is disclosed. The diffuser has a plurality of diffuser pipes circumferentially distributed about an axis of the compressor, each of the plurality of diffuser pipes extending from an inlet to an outlet and having a bend section between the inlet and the outlet, a low pressure side and an opposite high pressure side. A recirculation conduit defines a recirculation path from a first flow region to a second flow region in one or more of the plurality of the diffuser pipes, the first flow region having a greater static pressure than that of the second region, the recirculation conduit having a conduit inlet and a conduit outlet, at least the conduit outlet located within the low pressure side of one of the plurality of the diffuser pipes.

The invention relates to a blade assembly 30 for a large dimension axial fan 32 having a rotation axis X. The blade assembly of the invention comprises: a root structure 34 intended to mechanically connect the blade assembly to a hub 36; a blade, wherein at least one portion of the blade has a composite airfoil 46 comprising a fore semi-airfoil 48 and an aft flap 50, wherein: the semi-airfoil is intended to be assembled at a predefined pitch angle α.sub.c with respect to the hub 36 by means of the root structure; the flap 50 is mounted on the blade such that it can be fixed in a position comprised between a maximum deflection position and a minimum deflection position with respect to the pitch angle α.sub.c; and between the fore semi-airfoil and the aft flap a channel 54 is defined suitable for allowing a fluid flow from the face v to the back d of the composite airfoil. The invention further relates to a fan comprising a plurality of blades.

A compressor including a casing and an impeller arranged within the casing. The impeller is rotatable about an axis. A diffuser section is arranged within the casing. The diffuser section is positioned downstream from an outlet of the impeller and includes a first set of vanes disposed circumferentially about the diffuser section and a second set of vanes disposed circumferentially about the diffuser section. At least one vane in the second set of vanes includes an aspiration slot.

The present invention relates to a jet structure of a fan rotor, which comprises a fan wheel and at least one connecting channel. The fan wheel has a hub and plural blades disposed on the circumferential side of the hub. The hub has a top portion and a sidewall. Each of the blades has an upper surface and a lower surface which form a high-pressure zone and a low-pressure zone, respectively. The connecting channel is provided with at least one first inlet disposed in the high-pressure zone and at least one first outlet disposed in the low-pressure zone. The first inlet and the first outlet are a first end and a second end of the connecting channel, respectively. By means of the design of the present invention, the effect of noise reduction can be achieved.

An impeller includes a shroud including an inlet, a hub facing the shroud; and a plurality of blades disposed between the hub and the shroud and arranged circumferential direction along a circumference of the inlet. Wherein each of the plurality of blades has a slot which is positioned adjacent to the inlet.

The invention relates to a diffuser for a radial compressor, comprising a flow channel defined by a first side wall and a second side wall, a diffuser vane ring with a plurality of diffuser vanes that are at least partially arranged in the flow channel, each of the diffuser vanes having a pressure side and a suction side, a plurality of diffuser passages, said diffuser passages being formed between every two adjacent diffuser vanes of the plurality of diffuser vanes, and circulation openings, each circulation opening connecting the flow channel to a diffuser cavity, at least two circulation openings being associated with one diffuser passage, and a circulation opening associated with a diffuser passage being fluidically connected to another circulation opening associated with the same diffuser passage or to a circulation opening associated with another diffuser passage, via the diffuser cavity.