Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure and the second hairpin structure are made from different materials.

A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.

A method to produce a ceramic matrix composite with controlled surface characteristics includes: applying a scrim ply to a surface of a fiber preform, where the fiber preform includes silicon carbide fibers coated with boron nitride; infiltrating the fiber preform and the scrim ply with a slurry, thereby forming an impregnated ply on an impregnated fiber preform; infiltrating the impregnated fiber preform and the impregnated ply with a melt comprising silicon, and then cooling, thereby forming a ceramic matrix composite having a ceramic surface layer thereon, where the ceramic surface layer has a predetermined thickness and is devoid of boron; machining or grit blasting the ceramic surface layer to form an intermediate layer suitable for coating; and depositing an environmental barrier coating on the intermediate layer. Thus, a ceramic matrix composite coated with the environmental barrier coating is formed with the intermediate layer in between.

An electroformed heat exchanger suitable for use between rotating blades and seals in a stationary casing of a turbine engine. The heat exchanger comprising a non-electroformed carrier plate having a radial outer surface and a radial outer surface, an electroformed duct provided along the radial outer surface, an electroformed rail provided on the radial inner surface, and an electroformed stiffener formed by a portion of the electroformed duct and the electroformed rail.

A turbine comprises a turbine wheel for rotation within a turbine housing, the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle. A method for determining a width of a turbine nozzle for the turbine, comprises selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area. As used here, the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute. The method further comprises determining, in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area.

A gas turbine engine includes a fan and a rotor assembly. The rotor assembly includes a rotor, a plurality of magnets, and an annular retaining sleeve. The rotor includes a radially outer wall spaced apart from a central axis of the engine by an axially forward and an axially aft annular end wall. The magnets are located radially outward of the rotor and arranged on the outer wall in axial alignment with each other, the magnets being configured to move radially relative to each other and remain in contact with the outer wall in response to elastic deformation of the outer wall. The sleeve radially surrounds the magnets so as to structurally support and secure the magnets to the rotor, the sleeve being elastically deformable in the radial direction and configured to elastically deform based on the radial movement of the magnets.

The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.

A turbofan gas turbine engine includes, among other things, a fan section including a fan hub and an outer housing, the fan hub including a hub diameter supporting a plurality of fan blades, a turbine section including a fan drive turbine, and a geared architecture that interconnects the fan drive turbine and the fan hub, the geared architecture including a gear volume.

A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.

An article includes a substrate, a ceramic barrier coating, and a layer of networked ceramic nanofibers. The ceramic barrier coating is disposed on the substrate and has a porous columnar microstructure. The layer of networked ceramic nanofibers is disposed on the ceramic barrier layer and seals the pores of the porous columnar microstructure.