US Patent 11242155 Gas turbine engine compression system
Patent 11242155 was granted and assigned to Rolls-Royce on February, 2022 by the United States Patent and Trademark Office.
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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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Patent Number
112421550
Date of Patent
February 8, 2022
0Patent Application Number
164372840
Date Filed
June 11, 2019
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Patent Applicant
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Patent Jurisdiction
Patent Number
112421550
Date of Patent
February 8, 2022
0Patent Application Number
164372840
Date Filed
June 11, 2019
0Official Website
Patent Citations
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US Patent 11242155 Gas turbine engine compression system
Infobox
Is a
Patent applicant
Current assignee
Patent jurisdiction
Patent number
11242155
Date of patent
February 8, 2022
Patent application number
16437284
Date Filed
June 11, 2019
Patent citations
Patent primary examiner
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