Invention Application
- Patent Title: GAS TURBINE ENGINE FAN BLADE WITH AXIAL LEAN
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Application No.: US15894249Application Date: 2018-02-12
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Publication No.: US20180231020A1Publication Date: 2018-08-16
- Inventor: Mark J. WILSON , Gabriel GONZALEZ-GUTIERREZ , Marco BARALE , Benedict PHELPS , Kashmir S. JOHAL , Nigel HS SMITH
- Applicant: ROLLS-ROYCE plc
- Applicant Address: GB London
- Assignee: ROLLS-ROYCE plc
- Current Assignee: ROLLS-ROYCE plc
- Current Assignee Address: GB London
- Priority: GB1702383.9 20170214
- Main IPC: F04D29/38
- IPC: F04D29/38 ; F02K3/06

Abstract:
A fan blade for a gas turbine engine is arranged such that for any two points on its leading edge that are in the radially outer 40% of the blade span and are radially separated by at least 5% of the blade span, the radially outer of the two points is axially forward of the radially inner point. The radius of the leading edge of a given fan blade at the hub divided by the radius of the leading edge of the fan blade at the tip is less than or equal to 0.3. Such an arrangement may result in an improved operability range.
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