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公开(公告)号：US10961916B2
公开(公告)日：2021-03-30
申请号：US16443938
申请日：2019-06-18
Applicant: ROLLS-ROYCE plc
Inventor： Nicholas Howarth , Gareth M Armstrong
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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