A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine and fan blades. Each unitary turbine and fan blade includes a single turbine airfoil, a single fan airfoil positioned radially outward from the single turbine airfoil, and a midspan shroud segment defined between the single turbine airfoil and the single fan airfoil.

A method for manufacturing a blade in composite material having an added metal leading edge for gas turbine aeroengine, includes producing a blade body in composite material including in longitudinal direction, a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in longitudinal direction between a lower end present at the shank part in composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body in composite material.

A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.

A blade for turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction between a root end and a tip end and including an inner void extending from the root end in the radial direction, a root body integrally formed with the airfoil body, extending from the root end of the air foil body to a bottom end in the radial direction, and including a receiving slot extending from the bottom end in the radial direction and opening into the inner void of the air foil body, and an insert positioned in the receiving slot of the root body and including a plurality of through holes extending in the radial direction to form a fluid connection to the inner void of the air foil body.

This steam turbine comprises: a rotating shaft that extends along an axis; a plurality of rotor blades that are arranged in the circumferential direction and that extend in a radial direction from the outer circumferential surface of the rotating shaft; a casing body that covers the rotating shaft and the rotor blades from the outer circumference side; and a plurality of stationary blades that extend in the radial direction from a position on the inner circumferential surface of the casing body on the upstream side of the rotor blades and that are arranged in the circumferential direction. A plurality of microgrooves that extend in the steam flow direction are formed on the surface of the rotor blades and/or the stationary blades.

A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.

A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

A method for selectively adhering braze powders to a surface comprises applying a braze powder to a surface, and then directing a laser beam onto the braze powder while the laser beam moves along a predetermined path relative to the surface. The laser beam selectively heats the braze powder along the predetermined path such that the braze powder is sintered and bonded to the surface. Thus, a braze deposit is formed at one or more predetermined locations on the surface. After forming the braze deposit, excess braze powder, that is, the braze powder not selectively heated by the laser, is removed from the surface.

An outlet guide vane for a turbofan engine, which results in reduced noise. The outlet guide vane may comprise an aerofoil, the aerofoil comprising at least porous section, wherein the at least one channel or porous section is positioned near the leading edge of the aerofoil.

A method of manufacturing a component for a gas turbine engine includes applying a thermoplastic polymer sheet over a composite body for the component; applying a shield over part of the composite body, the shield terminating at an end which overlies the thermoplastic polymer sheet and defines an interface between shielded and unshielded regions of the component; and pressing the shield into the thermoplastic polymer sheet so that the thermoplastic polymer sheet deforms around the end of the shield, such that the exterior profile of the component at the interface between the shielded and unshielded regions is flush.