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US 2020/0049063 A1Published application
Advanced gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsMichael J WHITTLE, Pascal DUNNING, Roderick M TOWNES
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Abstract
A highly efficient gas turbine engine includes a fan which 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.
Claims21
A gas turbine engine for an aircraft comprising:
- an engine core comprising:
- a turbine, a combustor, and a compressor, the turbine comprising a first turbine and a second turbine and the compressor comprising a first compressor and a second compressor;
- a first core shaft connecting the first turbine to the first compressor;
- 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 second turbine comprises at least one ceramic matrix composite component;
- and
- the mass of ceramic matrix composite in the second turbine is in the range of from 2% to 15% of the total mass of the second turbine.
7 more elements
A gas turbine engine for an aircraft comprising:
- an engine core comprising:
- a turbine, a compressor, and a combustor;
- a core shaft connecting the turbine to the compressor;
- a fan comprising a plurality of fan blades;
- and
- a gearbox that receives an input from at least a part of the turbine and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, wherein:
- the turbine comprises at least one ceramic matrix composite component;
- and
- the mass of ceramic matrix composite in the turbine is in the range of from 1% to 15% of the total mass of the turbine.
6 more elements
Dependencies are inferred from the claim text.