| 摘要 |
<p>A turbomachine comprises an annular casing 10 and a bladed rotor which is rotatable within the casing. A region of the casing over which tips of the rotor blades 6 are swept is provided with a series of axially spaced circumferential grooves 16A-16E, at least two of the grooves having different depths from each other. The groove depths may decrease towards the trailing or leading edges 22, 20 of the rotor blades. The gaps 18A-18D between adjacent grooves may be substantially identical. The gap between adjacent grooves situated at between 30% and 50% of the axial blade chord, from the blade leading edge, may be slightly larger than between other adjacent grooves. The turbomachine may be a fan or compressor of a gas turbine engine.</p> |
