Is a
Patent attributes
Patent Applicant
Current Assignee
Patent Jurisdiction
Patent Number
Date of Patent
February 8, 2022
Patent Application Number
16437284
Date Filed
June 11, 2019
Patent Citations
Patent Primary Examiner
Patent abstract
A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. 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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