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US 2019/0154055 A1Published application
Turbofan engine's fan blade and setting method thereof
AssigneeGeneral Electric Company
InventorsASPI Rustom WADIA, Deepak Manohar Kamath, Daniel Waslo
Life of this patent
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Abstract
A turbofan engine comprising a compressor rotor, a plurality of main blades, the main blades are circumferentially mounted on the compressor rotor; a plurality of spinner blades, the spinner blades are circumferentially mounted on the compressor rotor, the spinner blades are located forward to the leading edge of the main blades; each spinner blade is circumferentially offset to a corresponding main blade.
Claims20
A turbofan engine, comprising:
- a compressor rotor;
- a plurality of main blades, the main blades are circumferentially mounted on the compressor rotor;
- a plurality of spinner blades, the spinner blades are circumferentially mounted on the compressor rotor, the spinner blades are located forward of the leading edge of the main blade;
- wherein each spinner blade is circumferentially offset to a corresponding main blade.
1 more element
A method for setting a turbofan engine's blade, comprising:
- circumferentially mounting a plurality of main blades on a compressor rotor;
- circumferentially mounting a plurality of spinner blades on the compressor rotor, wherein the spinner blades are located forward of the leading edge of the main blades;
- wherein the plurality of main blades and the plurality of spinner blades are circumferentially offset to one another.
Dependencies are inferred from the claim text.