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US 12,305,535 B2Granted
Turbine engine having a compressor with an inducer
AssigneeGeneral Electric Company
InventorsAntonio Guijarro Valencia, Scott Alan Schimmels, Steven Douglas Johnson
Life of this patent
Estimating the term…
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 blade, the blade including a blade leading edge and a blade trailing edge;
- a stator having an inner band, an outer band, and a vane extending between the inner band and the outer band, the vane being provided axially forward of the blade, with respect to the rotational axis, the vane including a vane leading edge and a vane trailing edge;
- a bleed air passage extending through the rotor and being located axially between the vane and the blade;
- and
- an inducer provided along the inner band, the inducer comprising:
- a nozzle having a nozzle inlet and a nozzle outlet, the nozzle outlet facing the bleed air passage, with at least one of the nozzle inlet or the nozzle outlet being provided entirely axially between the vane trailing edge and the blade leading edge;
- and
- a nozzle passage fluidly coupling the nozzle inlet to the nozzle outlet, the nozzle passage having a centerline that is locally non-perpendicular to the rotor, the nozzle passage being shaped to 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.
5 more elements
An airfoil assembly comprising:
- a band;
- an airfoil extending from the band, the airfoil having a leading edge and a trailing edge;
- and
- an inducer provided along the band, the inducer comprising:
- a nozzle having a nozzle inlet and a nozzle outlet, with at least one of the nozzle inlet or the nozzle outlet being provided entirely axially aft of the trailing edge;
- and
- a nozzle passage fluidly coupling the nozzle inlet to the nozzle outlet, the nozzle passage having a curved centerline extending from the nozzle inlet to the nozzle outlet.
4 more elements
An airfoil assembly comprising:
- a band including a first band surface and a second band surface opposite the first band surface;
- an airfoil extending from the band, the airfoil having a leading edge and a trailing edge;
- and
- an inducer provided along the band, the inducer comprising:
- a nozzle having a nozzle inlet and a nozzle outlet, the nozzle inlet extends radially outward from the first band surface at an angle that has an absolute value of greater than 0 degrees and less than or equal to 20 degrees;
- and
- a nozzle passage fluidly coupling the nozzle inlet to the nozzle outlet, the nozzle passage having a curved centerline extending from the nozzle inlet to the nozzle outlet.
4 more elements
Dependencies are inferred from the claim text.