Invention Grant
- Patent Title: Gas turbine engine compression system
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Application No.: US16437284Application Date: 2019-06-11
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Publication No.: US11242155B2Publication Date: 2022-02-08
- Inventor: Gareth M Armstrong , Nicholas Howarth
- Applicant: ROLLS-ROYCE plc
- Applicant Address: GB London
- Assignee: ROLLS-ROYCE plc
- Current Assignee: ROLLS-ROYCE plc
- Current Assignee Address: GB London
- Agency: Oliff PLC
- Priority: GB1903257 20190311
- Main IPC: B64D27/10
- IPC: B64D27/10 ; F02C3/06 ; F02K3/06 ; F02K3/068 ; F02C3/04 ; F01D5/28 ; F02C7/04 ; F02C3/107 ; B64D33/02
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.
Public/Granted literature
- US20200290743A1 GAS TURBINE ENGINE COMPRESSION SYSTEM Public/Granted day:2020-09-17
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