Swept compressor blade, compressor, and gas turbine including same

A compressor comprising:

• a plurality of compressor rotor disks mounted to a rotating shaft;
• and
• a plurality of compressor blades each coupled to the plurality of compressor rotor disks,
• wherein each compressor blade includes an airfoil including stacked sections having a predetermined thickness formed in a form of a closed curve connecting concave and convex curves, extending in a radial span between a hub and a shroud, extending in a direction of a chord line between a leading edge and a trailing edge, and extending in a thickness direction between a pressure surface and a suction surface,
• wherein the airfoil is formed with sections having a predetermined thickness stacked to be inclined in a radial direction, and includes a swept profile formed such that the leading edge and the trailing edge are inclined forward or rearward of the chord line, and
• wherein the swept profile includes a first area swept rearwards from the hub, a second area swept forwards from a position opposite to the first area to the shroud, and a third area that is not swept and is located between the first area and the second area.

A gas turbine comprising:

• a compressor configured to compress air by a plurality of compressor blades;
• a combustor configured to mix compressed air supplied from the compressor with a fuel for combustion;
• and
• a turbine including a plurality of turbine blades mounted in a turbine casing and configured to rotate the turbine blades with combustion gas discharged from the combustor,
• wherein each compressor blade includes an airfoil including stacked sections having a predetermined thickness formed in a form of a closed curve connecting concave and convex curves, extending in a radial span between a hub and a shroud, extending in a direction of a chord line between a leading edge and a trailing edge, and extending in a thickness direction between a pressure surface and a suction surface,
• wherein the airfoil includes sections having a predetermined thickness stacked to be inclined in a radial direction, and includes a swept profile formed such that the leading edge and the trailing edge are inclined forward or rearward of the chord line, and
• wherein the swept profile includes a first area swept rearwards from the hub, a second area swept forwards from a position opposite to the first area to the shroud, and a third area that is not swept and is located between the first area and the second area.