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US 12,698,715 B2Granted
Rotor blade with frangible spar for a gas turbine engine
AssigneeGeneral Electric Company
InventorsNicholas Joseph Kray, Nitesh Jain
Life of this patent
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Abstract
A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.
Claims20
A rotor blade for a gas turbine engine, the rotor blade comprising:
- a blade body formed of a first material;
- a first spar within a first portion of the blade body, the first spar formed of a second material that is different than the first material, the first spar having a first spar elongate body including a first spar notch, wherein the first spar notch defines a first frangible portion of the first spar;
- and
- a second spar within a second portion of the blade body, the second spar formed of the second material that is different than the first material, the second spar having a second spar elongate body including a second spar notch, wherein the second spar notch defines a second frangible portion of the second spar.
1 more element
Dependencies are inferred from the claim text.