Invention Grant
- Patent Title: Geared gas turbine engine
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Application No.: US17987516Application Date: 2022-11-15
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Publication No.: US11781491B2Publication Date: 2023-10-10
- Inventor: Nicholas Howarth , Gareth M Armstrong
- 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: GB 03261 2019.03.11
- Main IPC: F01D15/12
- IPC: F01D15/12 ; F02C7/36 ; F02C3/113
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.
Public/Granted literature
- US20230079630A1 GEARED GAS TURBINE ENGINE Public/Granted day:2023-03-16
Information query
