A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

A turbine wheel is provided with a groove having a bottom surface and a pair of side wall surfaces. The turbine wheel includes: a balance weight that is arranged in the groove, is insertable from any circumferential position of the opening of the groove, and has a through-hole opened toward one of the pair of side wall surfaces; and a retaining member that contacts the one of the pair of side wall surfaces in a state of being inserted in the through-hole of the balance weight, to thereby cause the balance weight to abut against the other one of the pair of side wall surfaces and be retained in the groove. The groove has engagement recesses provided at intervals in a circumferential direction at the bottom surface or an engagement protrusion fitted to one of fitting recesses provided at intervals in the circumferential direction at the bottom surface and protruding from the bottom surface. The balance weight has an engagement protrusion or an engagement groove that engages with one of the engagement recesses or the engagement protrusion of the groove, to thereby restrict a circumferential shift of the balance weight in the groove.

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body, aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. Rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body, aligned with the balancing weight slot. Balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

Turbomachine modules, for example for an aircraft, include a turbine nozzle having several sectors (S), each sector having guide vanes extending between inner and outer platform elements, at least one of the platform elements of each sector carrying, on the one hand, at least one sealing blade configured to ensure fluid sealing between the platform element and the adjacent structural element, and, on the other hand, a device configured to hold the at least one sealing blade in a sealing position. The device includes a leaf spring having a middle portion fixed to the platform element, and opposite end portions which are supported on the sealing blade carried by the platform element.

A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. Each of the first plurality of blades includes a blade root portion secured to the rotatable annular outer drum rotor. Each of the blade root portions includes one or more structural radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum and one or more axial retention features for axially retaining each of the blade root portions within the rotatable annular outer drum.

A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.

There is disclosed a blade for a gas turbine engine comprising an asymmetrical blade root.