Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

A compressor, which is mounted to a gas turbine and generates high temperature and high pressure compressed air and supplies the compressed air to a combustor, the compressor including: a plurality of main disks provided on an outer circumferential surface of a rotation shaft along a circumferential direction, and spaced apart from each other at predetermined intervals such that a portion of the compressed air flows toward the rotation shaft; and a reinforcing disk mounted to each space defined by the plurality of main disks spaced apart from each other, the reinforcing disk having the rotation shaft in common with the main disks, and being provided with a passage formed in a direction from an outer circumferential surface thereof toward the rotation shaft.

A rotor, a turbine, and a gas turbine including the same are provided. The rotor includes a pair of disks rotating about an imaginary central axis and arranged parallel to each other in an axial direction, a replaceable self-locking sealing assembly interposed between the pair of disks, and a fastening section disposed on the sealing assembly to fasten the sealing assembly to the disks. The disk includes a sealing slot disposed on an opposite surface to another adjacent disk and a head slot disposed outward from the sealing slot with respect to a radial direction of the to disk. The sealing assembly includes a main body with one end inserted into the sealing slot through the head slot from an outside of the disk and a sealing head disposed on another end of the main body to be seated on an inner wall of the head slot to restrict the main body from being moved.

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.

An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.

An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

A method of modulating cooling of gas turbine engine components includes the steps of identifying an input indicative of a usage rate for at least a first gas turbine engine component of a plurality of gas turbine engine components. A cooling system is operated for at least the first gas turbine engine component. The cooling system is moved between a higher cooling potential mode and a lower cooling potential mode based on the identified rate. A gas turbine engine is also disclosed.

A component is provided for a gas turbine engine. This component includes a monolithic body configured with an internal passage. The internal passage extends along a centerline within the monolithic body. The internal passage has a cross-sectional geometry perpendicular to the centerline. The cross-sectional geometry of at least a first portion of the internal passage has a teardrop shape.

The invention relates to a turbine rotor, of a low-pressure turbine of a turbine engine for example, including a first disk, an annular seal ring including a radial flange on which is formed a scalloping defined by a plurality of scallops offering a locally increased surface, circularly distributed, said radial flange being attached to the rotor between the first disk and the second disk and a flow circuit including at least one lunule, suitable to place into fluid communication a radially inner cavity and a radially outer cavity, the lunule being formed on the radial flange of the seal ring said lunule being provided on at least one scallop.