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US 12,454,917 B2Granted
Gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsPascal Dunning, Roderick M. Townes, Michael J. Whittle
Life of this patent
Estimating the term…
Abstract
A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
Claims20
A gas turbine engine for an aircraft comprising:
- an engine core comprising:
- a first turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor;
- a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, the second turbine, second compressor, and second core shaft being arranged to rotate at a higher rotational speed than the first core shaft;
- the gas turbine engine further comprising:
- a fan comprising a plurality of fan blades;
- and
- a gearbox that receives an input from the first core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the first core shaft, wherein:
- the total mass of the turbine, which includes the first turbine and the second turbine, is no greater than 17% of the total dry mass of the gas turbine engine, and a bypass ratio of the gas turbine engine at cruise conditions is in an inclusive range of from 12.5 to 16.
5 more elements
A gas turbine engine for an aircraft comprising:
- an engine core comprising:
- a first turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor;
- a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, the second turbine, second compressor, and second core shaft being arranged to rotate at a higher rotational speed than the first core shaft;
- the gas turbine engine further comprising:
- a fan comprising a plurality of fan blades;
- and
- a gearbox that receives an input from the first core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the first core shaft, wherein:
- the total mass of the turbine, which includes the first turbine and the second turbine, is no greater than 17% of the total dry mass of the gas turbine engine, and
- a turbine entry temperature, defined as the temperature at the inlet to a most axially upstream turbine rotor at a maximum power condition of the gas turbine engine, is at least 1800K.
6 more elements
Dependencies are inferred from the claim text.