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US 2020/0049067 A1Published application
Aircraft engine with high propulsive and thermal efficiency
AssigneeROLLS-ROYCE plc
InventorsRoderick M TOWNES, Pascal DUNNING, Michael J WHITTLE
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Abstract
A highly efficient gas turbine engine has a fan that 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.
Claims19
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 comprising a plurality of fan blades;
- and
- a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, wherein:
- at a maximum power condition, the ratio of the turbine entry temperature (K) to the fan speed in rpm is in the range of from 0.7 K/rpm to 2.0 K/rpm.
2 more elements
Dependencies are inferred from the claim text.