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US 2020/0370435 A1Published application
Gas turbine engine core arrangement
AssigneeROLLS-ROYCE plc
InventorCraig W. BEMMENT
Life of this patent
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Abstract
A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core, the fan including a plurality of fan blades, wherein the gas turbine engine is configured such that a flow velocity ratio between a first flow velocity at an exit of the engine core and a second flow velocity at an inlet of the engine core is within a range from around 0.82 to around 1.1 at cruise conditions.
Claims9
1-10. (canceled)
A method of operating a gas turbine engine on an aircraft, the gas turbine engine comprising:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
- and
- a fan located upstream of the engine core, the fan comprising a plurality of fan blades,
- wherein the method comprises operating the gas turbine engine to provide propulsion under cruise conditions such that a flow velocity ratio between a first flow velocity at an exit of the engine core and a second flow velocity at an inlet of the engine core is within a range from 0.82 to 1.1.
1 more element
Dependencies are inferred from the claim text.