A compressor for a gas turbine engine is disclosed. The compressor includes a first compression stage mounted for rotation about a central axis that includes a plurality of first-stage blades. The compressor also includes a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage. The second compression stage includes a plurality of second-stage blades.

An impeller includes a metallic inducer portion and a polymeric exducer portion connected to the metallic inducer portion. The metallic inducer portion includes an inducer hub, inducer blades attached to the inducer hub, and an inducer coupling on an end of the inducer hub. The polymeric exducer portion includes an exducer hub, exducer blades attached to the exducer hub, and an exducer coupling on an end of the exducer hub. The exducer coupling connects to the inducer coupling.

The present disclosure generally relates to rotary turbomachinery methods and integrated processes requiring high-energy efficiency. In one embodiment, the present invention relates to rim-rotor configurations enabling long-term survival under conditions of either high temperature or oxidation resistance or saturated fluid abrasion.

An impeller includes a metallic inducer portion and a polymeric exducer portion connected to the metallic inducer portion. The metallic inducer portion includes an inducer hub, inducer blades attached to the inducer hub, and an inducer coupling on an end of the inducer hub. The polymeric exducer portion includes an exducer hub, exducer blades attached to the exducer hub, and an exducer coupling on an end of the exducer hub. The exducer coupling connects to the inducer coupling.

A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

A compressor wheel (1) of a radial compressor (2) of an exhaust-gas turbocharger (3), having a hub (8); and having two blade rows (9, 10) which are arranged adjacent to one another on the hub (8), a first blade row (9) forming the leading blade row, and the adjacent, second blade row (10) forming the trailing blade row, wherein the number of blades (11) of the first blade row (9) is equal to the number of blades (12) of the second blade row (10).

A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented.

A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented.

A rotor assembly is provided and includes a two-piece rotor impeller and a rotor shaft. The two-piece rotor impeller includes a blade section and a forward section, which is connected to the blade section. The rotor shaft includes an aft section at which the rotor shaft terminates. The aft section is directly attached to the forward section of the rotor impeller. The blade section includes a converging blade configured to converge to a point with a minimized internal diameter (ID).

A rotor assembly is provided and includes a two-piece rotor impeller and a rotor shaft. The two-piece rotor impeller includes a blade section and a forward section, which is connected to the blade section. The rotor shaft includes an aft section at which the rotor shaft terminates. The aft section is directly attached to the forward section of the rotor impeller. The blade section includes a converging blade configured to converge to a point with a minimized internal diameter (ID).