Rotor for a compressor of a gas turbine

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.

主权项

1. 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 wherein a chord is defined between the leading edge and the trailing edge; wherein:
each of the blades extends from its hub away from the rotatable support;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;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;a distance A1 is defined as the distance between lines projected from the leading edges of two adjacent blades and a distance A2 is defined as the distance between lines projected from the trailing edges of the two adjacent blades, the ratio A2/A1 being greater than 2.2;an axial chord of the at least one of the blades is defined by a projection of the chord onto the axis of rotation and has an axial chord length; andfor the at least one of the blades the difference between the trailing-edge-hub-radius and the leading-edge-hub-radius is greater than 25 percent of the axial chord length.