Invention Grant
- Patent Title: Gas turbine engine fan blade
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Application No.: US15894240Application Date: 2018-02-12
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Publication No.: US10473112B2Publication Date: 2019-11-12
- Inventor: Nigel H S Smith , Mark J. Wilson , Gabriel Gonzalez-Gutierrez , Marco Barale , Benedict Phelps , Kashmir S. Johal
- Applicant: ROLLS ROYCE plc
- Applicant Address: GB London
- Assignee: Rolls-Royce plc
- Current Assignee: Rolls-Royce plc
- Current Assignee Address: GB London
- Agency: Duane Morris LLP
- Priority: GB1702382.1 20170214
- Main IPC: F04D29/38
- IPC: F04D29/38 ; F02K3/06

Abstract:
A fan blade is provided with an aerofoil portion for which, at radii between 20% and 40% of the blade span, the location of the position of maximum thickness along the camber line is at less than a defined percentage of the total length of the camber line. For all cross-sections through the aerofoil portion at radii greater than 70% of the blade span, the location of the position of maximum thickness along the camber line is at more than a defined percentage of the total length of the camber line. The geometry of the fan blade may result in a lower susceptibility to flutter.
Public/Granted literature
- US20180231018A1 GAS TURBINE ENGINE FAN BLADE Public/Granted day:2018-08-16
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