Geared turbofan engine
AssigneeROLLS-ROYCE plc
InventorClive Breen
Life of this patent
Estimating the term…
Abstract
A gas turbine engine for an aircraft, includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan assembly located upstream of the engine core; and a gearbox receiving an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft, wherein the fan assembly has fan blades mounted around a hub, the fan blades having blade tips defining an outer diameter of the fan assembly of from around 220 cm to around 400 cm, the hub having slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the fan blades is within the range of around 0.45 to around 0.7.
Claims15
A gas turbine engine for an aircraft, comprising:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
- a fan assembly located upstream of the engine core;
- and
- a gearbox that receives an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft,
- wherein the fan assembly comprises a plurality of fan blades mounted around a hub, the fan blades having blade tips defining an outer diameter of the fan assembly of from around 220 cm to around 400 cm, the hub comprising a plurality of slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the plurality of fan blades is within a range of around 0.45 to around 0.7.
A gas turbine engine for an aircraft, comprising:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
- a fan assembly located upstream of the engine core;
- and
- a gearbox that receives an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft,
- wherein the fan assembly comprises a plurality of fan blades mounted around a hub, a hub-to-tip ratio of the fan assembly being between around 0.2 and 0.4, the hub comprising a plurality of slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the plurality of fan blades is within a range of around 0.45 to around 0.7.
Dependencies are inferred from the claim text.