US Patent 12071901 Geared gas turbine engine
Patent 12071901 was granted and assigned to Rolls-Royce PLC on August, 2024 by the United States Patent and Trademark Office.
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US Patent 12071901 Geared gas turbine engine
Article
Patent abstract
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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Patent Applicant
Current Assignee
Patent Jurisdiction
Patent Number
Patent Inventor Names
Gareth M Armstrong0
Nicholas Howarth0
Date of Patent
August 27, 2024
0Patent Application Number
182366660
Date Filed
August 22, 2023
0Patent Citations
Patent Primary Examiner
CPC Code
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