Methods, apparatus, systems, and articles of manufacture are disclosed to adjust a pitch axis of a blade of an engine. An example blade apparatus includes: a hub to facilitate movement of blades in an engine, the engine having a radial center line; and a trunnion connected to the hub. The example trunnion includes a slot to accommodate a first blade, and at least one of the trunnion or the first blade is positioned with at least one of a tilt or a lean with respect to the radial center line to form a pitch axis offset from the radial center line such that the pitch axis is not parallel to or co-linear with the radial center line. The example hub is to rotate the first blade about the pitch axis.

A blade assembly for a gas turbine engine includes a rotor, a stator, a seal plate, and a sealing member. The rotor includes a rotor blade and a rotor disc. The rotor disc defines a bucket groove which receives a cooling fluid from a first cavity upstream of the rotor. The sealing member includes a control arm. The sealing member and the rotor define a flow cavity therebetween in fluid communication with an aperture of the seal plate. The flow cavity receives the cooling fluid flowing through the bucket groove and the aperture. The control arm and the seal plate define a gap therebetween fluidly communicating the flow cavity with a second cavity between the stator and the rotor. The control arm deflects at least a portion of the cooling fluid entering the flow cavity.

A turbine rotor blade root is additively manufactured and includes a shank having a radially extending chamber defined therein. A blade mount is at a radial inner end of the shank. The blade mount has a hollow interior defined therein with the hollow interior in fluid communication with the radially extending chamber. A lattice support structure is disposed within the hollow interior of the blade mount.

A jig for assembling and extracting a blade root spring for fixing a rotor blade to a rotor includes: an extrusion mechanism for extruding the blade root spring or an extrusion rod pressed against the blade root spring; and a base plate to which the extrusion mechanism is fixed. The base plate is formed with a first groove for receiving a reaction force which is obtained when the extrusion mechanism extrudes the extrusion rod toward the blade root spring to extrude and assemble the blade root spring or to extract the blade root spring.

A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.

A structure for assembling turbine blade seals, a gas turbine including the same, and a method of assembling turbine blade seals are provided. The structure for assembling turbine blade seals includes a turbine blade including an airfoil, a platform, and a root, a turbine rotor disk to which the root of the turbine blade is mounted, a seal plate mounted between the platform and one side of the turbine rotor disk to seal a cooling channel defined within the root and the platform, an insertion pin inserted through the turbine rotor disk and the seal plate to fix the seal plate to the turbine rotor disk, and a retainer configured to fix the insertion pin and to prevent the insertion pin from falling out.

A turbine rotor includes a disc with cavities, a plurality of blades, each with a root received in one of the cavities, and an axial retention system including a first series and a second series of strips circumferentially distributed around an axis of the rotor, the first and the second series being axially superimposed and arranged such that at least two strips circumferentially adjacent to the first series are axially superimposed on a strip of the second series and each strip of the first and second series is arranged opposite a cavity of the disc so as to axially block the root of a blade.

Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.

A bladed disc for a rotating machine comprising a central disc that rotates about a central axis, the central disc having a series of blades arranged around its periphery; the blades have dovetail roots which engage with slots on the central disc; the bladed disc being configured so that there is a pre-loading force between the blades and the central disc such that each blade is forced away from the central axis of the bladed disc; and wherein the pre-loading force is equal or greater than 40% of the maximum centrifugal force applied to the blade during a flight cycle.

In a turbine wheel, each of seal plates is formed from an elastic plate member whose radially intermediate portion is curved projecting toward one axial end surfaces of turbine blades and a turbine disk. The seal plate includes: an assembly recessed portion recessed in a direction getting closer to the one axial end surfaces, near a radially outer end of the plate; and a disassembly protrusion projecting in a direction getting away from the one axial end surfaces, near a radially inner end of the plate. When the recessed portion is pressed for attaching the plate, a tip end of the recessed portion comes into contact with the one axial end surface of each turbine blade or the disk. The plate is accordingly inhibited from being excessively deformed. Thus, the plate is blocked from being plastically deformed, and is precluded from coming off the wheel.