Efficient gas turbine engine installation and operation
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United States of America Patent
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Oct 4, 2022
Grant Date -
Jul 8, 2021
app pub date -
Mar 25, 2021
filing date -
Mar 11, 2019
priority date (Note) -
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Abstract
A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.
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