Invention Grant
- Patent Title: Gas turbine engine compression system with core compressor pressure ratio
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Application No.: US17562609Application Date: 2021-12-27
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Publication No.: US11584532B2Publication Date: 2023-02-21
- 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 ; F02C7/04 ; B64D33/02 ; F01D5/28 ; F02C3/107
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
- US20220119120A1 GAS TURBINE ENGINE COMPRESSION SYSTEM Public/Granted day:2022-04-21
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