| 摘要 |
<p>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. A second region 22 extends obliquely with respect to the radial direction and the adjacent part of the aerofoil surface 2. The second region 22 defines a winglet, and serves to increase the width of the chamber 12 towards the trailing edge 8 of the blade.</p> |
