Is a
Patent attributes
Patent Applicant
Current Assignee
Patent Jurisdiction
Patent Number
Date of Patent
February 4, 2020
Patent Application Number
16437356
Date Filed
June 11, 2019
Patent Citations Received
Patent Primary Examiner
Patent 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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