Turbine engine having a compressor with an inducer
AssigneesGeneral Electric Company, General Electric Deutschland Holding GmbH
InventorsAntonio Guijarro Valencia, Scott Alan Schimmels, Steven Douglas Johnson
Life of this patent
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Abstract
A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.
Claims20
A turbine engine comprising:
- a rotor rotatable about a rotational axis and having a plurality of sets of circumferentially arranged blades axially spaced along the rotational axis from one another;
- a stator having an inner band, an outer band, and a plurality of sets of circumferentially arranged vanes extending between the inner band and the outer band, with each set of circumferentially arranged vanes being provided axially between two sets of circumferentially arranged blades;
- a plurality of circumferentially spaced bleed air passages extending through the rotor and being located between an axially adjacent set of vanes and blades;
- and
- an inducer located axially between the axially adjacent set of vanes and blades, the inducer comprising:
- a set of circumferentially spaced nozzles having a nozzle inlet facing the stator and a nozzle outlet facing the plurality of circumferentially spaced bleed air passages;
- and
- a nozzle passage fluidly coupling the nozzle inlet to the nozzle outlet;
- wherein the nozzle passage defines a centerline that is locally non-perpendicular to the rotor to thereby turn a passage airflow in the nozzle passage from having a first circumferential component at the nozzle inlet to having a second circumferential component at the nozzle outlet, the second circumferential component being opposite the first circumferential component.
An airfoil assembly circumferentially extending across a portion of an axial centerline, the airfoil assembly comprising:
- a band;
- and
- an inducer operably coupled to the band and comprising:
- a set of circumferentially spaced nozzles having a nozzle inlet and a nozzle outlet;
- and
- a nozzle passage fluidly coupling the nozzle inlet to the nozzle outlet;
- wherein the nozzle passage defines a centerline that is locally non-perpendicular to the axial centerline to thereby turn a passage airflow in the nozzle passage from having a first circumferential component at the nozzle inlet to having a second circumferential component at the nozzle outlet, the second circumferential component being opposite the first circumferential component.
Dependencies are inferred from the claim text.