The rotor disk (3B) for a compressor comprises, relative to the rotational axis of the disk: a radial web (4), blades (8) at the outer periphery of the web, a bore (5) at the inner periphery of the web, and a cylindrical side wall (12) extending the web in the vicinity of the ter periphery of same and having an air supply port (18), anda centripetal air collection device (15). Advantageously, the device (15) comprises a cylindrical support (23) and at least one air supply tube (16), the inlet of which is turned towards the port (18) and the outlet of which is turned towards the bore (5) in the web, the disk comprising an inner radial flange (40) extending from the cylindrical side wall (12), the cylindrical support (23) of the device (15) being attached to said inner radial flange (40), and a ring (30) extending from the web (4), the cylindrical support (23) being centred on the ring (30).

A stator vane assembly including an inner diameter platform. The assembly also includes an outer diameter platform defining an air inlet orifice extending radially therethrough. Further included is an airfoil extending between the inner diameter platform and the outer diameter platform, the airfoil having a hollow portion therein defining a serpentine cooling airflow path fluidly coupled to the air inlet orifice. Yet further included is a collar extending radially outwardly from the outer diameter platform and positioned adjacent the air inlet orifice, the collar extending to a non-uniform radial distance. The assembly also includes a turn cover operatively coupled to the collar.

Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a platform lip extending axially from the platform portion; and a plurality of voids disposed along a surface of the platform lip.

A rotor assembly, especially for a gas turbine, includes at least a first rotor disc and a second rotor disc, the two rotor discs are arranged directly next to each other. The first rotor disc has a center through hole and the second rotor disc has no center through hole but a rotor disc center. A flow restrictor assembly which restricts the effective flow cross section of the center through hole of the first disc is used to control or to adjust the cooling air through gaps of a form-fitting torque transmitting device.

A turbine disc having a radius and a circumference is provided. The turbine disc includes a central aperture and a plurality of cooling channels circumferentially spaced about the central aperture such that the cooling channels are in flow communication with the central aperture. Each of the cooling channels has a radially inner end, a radially outer end, and a lengthwise axis that is curved between the radially inner end and the radially outer end.

According to exemplary embodiments, a rotor off-take assembly is provided by positioning an angled hole or aperture in a stator assembly. This angled hole provides improved pressure recovery and utilizes higher dynamic pressure to drive the bleed air flow into the off-take cavity.

A compressor for a turbomachine, with at least one rotor disc and a space that is at least partially enclosed by the at least one rotor disc and that is arranged axially in front of or behind the at least one rotor disc, wherein vortex reducers are arranged inside the space, wherein the vortex reducers are connected to the structural components in a form-fitted and/or in a frictionally engaged manner partially via first scallops at a first structural component and partially via second scallops at a second structural component that is adjacent to the first structural component in the axial direction, wherein the first scallops and/or second scallops are arranged at a retaining ring, which can be connected or is connected to the first rotor disc and/or the second rotor disc. What is further described is a method for mounting a compressor.

An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a passage. The cooling hole can include a laid back section where a coating can be applied. The method can include forming the cooling hole in the component and applying the coating to the component to maintain a specific geometry.

A turbine blade includes a platform, a blade airfoil attached to one side of the platform, a blade root attached to the other side of the platform, a manifold attached to the blade root. The blade root defines a first cooling passage and a second cooling passage. The manifold includes an outer wall, a first compartment having a first flow area defined by a first aperture formed at the outer wall, and a second compartment having a second flow area defined by a second aperture formed at the outer wall. The first compartment meters a non-zero first flow of cooling air to the first cooling passage through the first flow area. The second compartment meters a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area.

A cooling structure for a turbine includes a plurality of disks configured to rotate integrally with blades, the disks being arranged along a rotational axis; and the disks have disk holes defined therein and arranged in a circumferential direction for supplying cooling air for cooling the blades to downstream disks. At least one of the disk holes is set such that, when a rotational direction of the disk is defined as a positive direction and a direction opposite the rotational direction is defined as a negative direction, an outlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an outlet of the disk hole is smaller than an inlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an inlet of the disk hole.