| 摘要 |
A blade for a rotor, such as a turbine rotor of a gas turbine engine has a squealer tip comprising a peripheral wall 14 which defines a cavity 12. A first region 18 of the peripheral wall 14 extends radially, with its outer surface forming a continuation of the adjacent aerofoil surface 4 of the blade. At least one second region 22, 36 extends obliquely with respect to the radial direction and the adjacent part of the aerofoil surface 2. The at least one second region 22, 36 defines a winglet, and serves to increase the width of the chamber 12 towards the trailing edge 8 of the blade.
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