| US 7,354,243 B2 | ||
| Axial compressor blading | ||
| Neil W. Harvey, Derby (United Kingdom) | ||
| Assigned to Rolls-Royce, PLC, London (United Kingdom) | ||
| Filed on Aug. 16, 2006, as Appl. No. 11/504,697. | ||
| Claims priority of application No. 0518628.3 (GB), filed on Sep. 13, 2005. | ||
| Prior Publication US 2007/0059177 A1, Mar. 15, 2007 | ||
| Int. Cl. F01D 9/02 (2006.01); F01D 5/14 (2006.01) | ||
| U.S. Cl. 415—191 [415/211.2; 415/914; 416/193 A] | 12 Claims |
| 1. A row of aerofoil members for an axial compressor, the row comprising:
a plurality of radially extending aerofoils; and
circumferentially extending radially inner and outer end walls,
wherein at least one of the end walls has a profile defined by a plurality of perturbations at a succession of axial positions,
wherein at least a first terturbation is not in phase with a second perturbation,
wherein at least one of the perturbations is a sinusoid, the or each sinusoid being defined by its phase and its amplitude
relative to the baseline profile of the or each end wall, the pitch of the or each sinusoid being the same as the pitch of
the aerofoil members, the or each end wall being further shaped to provide smooth transitions between successive perturbations.
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