| 摘要 |
In a rotor blade or guide vane ring, for a gas turbine, the transition between a surface 3, of the blade/vane aerofoil 2, and a platform 4, at an end of the aerofoil, is shaped to reduce stress due to flexural torque. The transition exhibits variable curvature and may comprise at least two curves of different radii, R1,R3, the radius of the curve nearest the surface of the aerofoil being larger than the radius of the curve nearest to the platform. The transition may comprise two curves of different radii separated by a straight line section, or it may form a section of an ellipse. The platform may form part of the blade carrier of an integral bladed rotor or of a segmented guide vane ring having a shroud. |
