Invention Grant
US07946825B2 Turbofan gas turbine engine fan blade and a turbofan gas turbine fan rotor arrangement
有权
Turbofan燃气涡轮发动机风扇叶片和涡轮风扇燃气轮机风扇转子装置
- Patent Title: Turbofan gas turbine engine fan blade and a turbofan gas turbine fan rotor arrangement
- Patent Title (中): Turbofan燃气涡轮发动机风扇叶片和涡轮风扇燃气轮机风扇转子装置
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Application No.: US12585777Application Date: 2009-09-24
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Publication No.: US07946825B2Publication Date: 2011-05-24
- Inventor: David J Tudor
- Applicant: David J Tudor
- Applicant Address: GB London
- Assignee: Rolls-Royce, plc
- Current Assignee: Rolls-Royce, plc
- Current Assignee Address: GB London
- Agency: Oliff & Berridge, PLC
- Priority: GB0513187.5 20050629
- Main IPC: F01D5/20
- IPC: F01D5/20
Abstract:
A fan blade is provided having a root portion and an aerofoil portion that has a leading edge, a trailing edge and a tip remote from the root portion. A concave pressure surface extends from the leading edge to the trailing edge and a convex suction surface extends from the leading edge to the trailing edge. A portion of the tip of the aerofoil portion between the leading edge and the trailing edge of the aerofoil portion is thinner than the remainder of the tip. The portion of the tip of the aerofoil portion is spaced from the leading edge and is spaced from the trailing edge. The portion of the tip of the aerofoil portion has a recess arranged on the concave pressure surface such that the portion of the tip of the aerofoil portion is thinner than the remainder of the tip.
Public/Granted literature
- US20100014984A1 Turbofan gas turbine engine fan blade and a turbofan gas turbine fan rotor arrangement Public/Granted day:2010-01-21
Information query
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