GAS TURBINE ENGINE FAN AND NOZZLE GEOMETRY
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United States of America Patent
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Issued Date -
Jun 25, 2020
app pub date -
May 14, 2019
filing date -
Dec 21, 2018
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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 located upstream of the engine core, the fan having a plurality of fan blades, wherein a fan tip radius of the fan is measured between a centreline of the engine and an outermost tip of each fan blade at its leading edge; and a nacelle surrounding the fan and the engine core and defining a bypass exhaust nozzle, the bypass exhaust nozzle having an inner radius. An inner bypass to fan ratio of:
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