US Patent 10981663 Aero engine flow rate
Patent 10981663 was granted and assigned to Rolls-Royce on April, 2021 by the United States Patent and Trademark Office.
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Patent abstract
A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan defining a fan tip radius at the fan face; wherein a downstream blockage ratio is defined as:
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Patent Inventor Names
Michael C Willmot0
Richard G Stretton0
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Patent Applicant
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Patent Jurisdiction
Patent Number
109816630
Date of Patent
April 20, 2021
0Patent Application Number
169347670
Date Filed
July 21, 2020
0Official Website
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US Patent 10981663 Aero engine flow rate
Infobox
Is a
Patent applicant
Current assignee
Patent jurisdiction
Patent number
10981663
Date of patent
April 20, 2021
Patent application number
16934767
Date Filed
July 21, 2020
Patent citations
Patent primary examiner
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