An assembly of a rotating component and a rotationally stationary component includes a first bearing portion located at the rotating component and rotatable therewith, and a second bearing portion located at the rotationally stationary component. The second bearing portion is supported at the rotationally stationary component and rotatably with the rotating component when in contact with the first bearing portion. The first bearing portion and the second bearing portion define a single point contact therebetween.

A rotor assembly comprises a rotor having annular flange including a plurality of protrusions axisymmetrically disposed about the annular flange, each protrusion having a mounting aperture for selectively receiving a balancing feature, and a plurality of slots axisymmetrically disposed about the circumference of the annular flange between adjacent protrusions. Each slot has a pair of converging flat portions extending axially inwardly from an adjacent protrusion end, an inner flat portion at an inner end of each slot, and a pair of curved portions respectively joining each converging flat portion to the inner flat portion in each slot. Each slot has a depth at least as great as an adjacent mounting aperture depth extending normally from the adjacent protrusion end to a far end of the corresponding mounting aperture.

A balance adjustment method for a rotor includes an imbalance acquisition step of acquiring imbalance position and amount of the rotor after a first balance correction step of correcting balance of the rotor by cutting a compressor wheel side, an excision target section determination step of determining, based on the imbalance position and amount of the rotor, an excision target range including an imbalance correction position of the turbine wheel and a removal amount in the excision target range, and a second balance correction step of correcting the balance of the rotor by repeatedly irradiating the excision target range determined in the excision target section determination step with laser light from a laser marker device to remove by the removal amount from the turbine wheel.

The method of assembling the rotor assembly can include obtaining geometrical reference values about the individual rotor components, based on the geometrical reference values, determining a combination of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence; and assembling the rotor components to one another in said determined combination of relative circumferential positions, into the rotor assembly.

An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.

An exhaust turbocharger turbine wheel can include a hub that includes a nose, a backdisk with a shaft joint portion, and a rotational axis; blades that extend from the hub to define exhaust flow channels where each of the blades includes a leading edge, a trailing edge, a hub profile, a shroud profile, a pressure side, and a suction side; where the backdisk includes an outer perimeter radius measured from the rotational axis of the hub, an intermediate radius at the shaft joint portion measured from the rotational axis of the hub, and an annular recess disposed between the intermediate radius and the outer perimeter radius and defined in part by three-dimensional bolster regions, where each of the three-dimensional bolster regions includes a footprint and a height measured at least in part in a direction of the rotational axis of the hub.

A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

A method for balancing a set of blades intended to be arranged on a bare disc of an aircraft engine, the bare disc comprising a defined number of numbered cells (ai) intended to receive the same defined number of blades, which can have a spread of mass, the method comprising the following steps:—sorting the blades by monotonic order of their mass (mi) to form an ordered set of blades,—separating the ordered set of blades in a balanced manner into four lobes constituted by a first large lobe, by a second large lobe, by a first small lobe and by a second small lobe, the blades being classified into each lobe according to a current placement order, and—arranging the four lobes on the bare disc by making the current placement order of the blades correspond to the numbered cells of the bare disc.

A manufacturing system manufactures a rotating assembly by attaching a plurality of attached target members in a circumferential direction of a rotating main body portion. A storage member capable of storing the plurality of attached target members is placed on a stand. A measurement device measures a physical amount of the attached target member An attachment device attaches one attached target member to a predetermined position in the circumferential direction of the rotating main body portion based on the physical amount measured by the measurement device A transfer device transfers the attached target member.

A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.