| 摘要 |
A rotor, for a compressor of a gas turbine, comprising a rotatable support for rotation about an axis of rotation and a plurality of blades. Each blade comprising a hub, a leading edge and a trailing edge and a chord is defined between the leading edge and the trailing edge. Each of the blades extends from its hub away from the rotatable support and at least one of the blades has a hub-thickness to chord ratio greater than 10 percent. The leading edge of the at least one of the blades at its hub is positioned at a leading-edge-hub-radius from a position of the axis of rotation and the trailing edge of the at least one of the blades is positioned at its hub at a trailing-edge-hub-radius from the position of the axis of rotation. The trailing-edge-hub-radius is greater than the leading-edge-hub-radius. |
