Efficient gas turbine engine installation and operation
Number of patents in Portfolio can not be more than 2000
United States of America
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Feb 4, 2020
Grant Date -
N/A
app pub date -
Jun 11, 2019
filing date -
Jun 11, 2019
priority date (Note) -
In Force
status (Latency Note)
Importance
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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