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US 11,028,697 B2Granted
Low speed fan for gas turbine engines
AssigneeRaytheon Technologies Corporation
InventorGary D. Roberge
Life of this patent
Estimating the term…
Abstract
A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.
Claims18
A fan section for a gas turbine engine, comprising:
- a rotor disk made of metal;
- and
- a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece and extending radially outward from the rotor disk with respect to an engine axis, each airfoil having a collar bonded to a radially outermost surface of the rotor disk, the collar having an outer surface that is flush with an exterior surface of the airfoil, wherein each collar fixedly secures a respective one of the plurality of airfoils to the rotor disk, and each of the plurality of airfoils being made at least partially of an organic matrix composite, and wherein each collar is positioned around a respective base of a respective one of the plurality of airfoils and extends radially above the radially outermost surface of the rotor disk.
A gas turbine engine, comprising:
- a fan section having a rotor disk made of metal, and a plurality of airfoils, the airfoils being fixedly attached to and supported by the rotor disk as a single unitary piece and extending radially outward from the rotor disk with respect to an engine axis, each airfoil of the plurality of airfoils having a collar bonded to a radially outermost surface of the rotor disk, the collar having an outer surface that is flush with an exterior surface of the airfoil, wherein each collar fixedly secures a respective one of the plurality of airfoils to the rotor disk, each of the plurality of airfoils being made at least partially of an organic matrix composite, and wherein each collar is positioned around a respective base of a respective one of the plurality of airfoils and extends radially above the radially outermost surface of the rotor disk;
- a compressor section downstream from the fan section;
- a combustor downstream from the compressor section;
- and
- a turbine section downstream from the combustor and in mechanical communication with the fan section and compressor section via an engine shaft.
2 more elements
A method of forming a fan section of a gas turbine engine, the method comprising:
- providing a rotor disk made of metal;
- and
- fixedly attaching a plurality of airfoils to the rotor disk with a plurality of collars, each airfoil being made at least partially of organic composite matrix and each collar being bonded to a radially outermost surface of the rotor disk and each collar having an outer surface that is flush with an exterior surface of the airfoil, wherein each collar is positioned around a respective base of a respective one of the plurality of airfoils and extends radially above the radially outermost surface of the rotor disk.
Dependencies are inferred from the claim text.