Geared turbofan with four star/planetary gear reduction
AssigneeRaytheon Technologies Corporation
InventorsFrederick M. Schwarz, William G. Sheridan, Michael E. McCune, Gabriel L. Suciu
Life of this patent
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Abstract
A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.
Claims20
A turbofan engine comprising:
- a fan including a fan rotor having fan blades, and housing enclosing said fan rotor and said blades;
- a turbine rotor driving said fan rotor;
- an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and four intermediate gears that engage said sun gear and said ring gear, a gear ratio of said gear reduction is greater than 3.06;
- wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;
- a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said housing compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0;
- and
- wherein there is a primary oil supply supplying oil to journal bearings that support said intermediate gears.
A turbofan engine comprising:
- a fan including a fan rotor having fan blades, and a housing enclosing said fan rotor and said blades;
- a turbine rotor driving said fan rotor;
- an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and four intermediate gears that engage said sun gear and said ring gear, a gear ratio of said gear reduction is greater than 3.06;
- wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;
- a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said housing compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0;
- and
- wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.
A turbofan engine comprising:
- a fan including a fan rotor having fan blades, and a housing enclosing said fan rotor and said blades;
- a turbine rotor driving said fan rotor;
- and
- an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and no more than four intermediate gears that engage said sun gear and said ring gear;
- wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;
- a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said housing compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0;
- and
- wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle, and wherein said fan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
Dependencies are inferred from the claim text.