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US 2017/0284422 A1Published application
Gas turbine engine fan assembly
AssigneeROLLS-ROYCE plc
InventorRory D. STIEGER
Life of this patent
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Abstract
A fan assembly for a gas turbine engine. The assembly includes a hub and a plurality of blades projecting from the hub. The hub includes an inlet aperture located adjacent a blade root. The inlet aperture is in fluid communication with a passage extending along at least part of a span of the blade, and communicates with an outlet provided on an exterior of the blade, radially outwardly of the inlet.
Claims20
A fan assembly for a gas turbine engine, the assembly comprising:
- a hub and a plurality of blades projecting from the hub;
- wherein the hub comprises an inlet aperture located adjacent a blade root, the inlet aperture being in fluid communication with a passage extending along at least part of a span of the blade, wherein the passage communicates with an outlet provided on an exterior of the blade, radially outwardly of the inlet.
Dependencies are inferred from the claim text.