Is a
Patent attributes
Patent Applicant
Current Assignee
Patent Jurisdiction
Patent Number
Date of Patent
July 11, 2023
0Patent Application Number
177318770
Date Filed
April 28, 2022
0Patent Citations
Patent Primary Examiner
CPC Code
A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. 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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