Gas turbine for aircraft

A gas turbine for an aircraft comprising:

• a rotor which is capable of rotating about an axis;
• blades each including a blade body extending outward from the rotor in a radial direction of the rotor, a blade shroud formed on a distal end of the blade body, and a fin protruding from an outer peripheral surface of the blade shroud;
• a casing surrounding the rotor and the blades so as to form gaps between the casing and the fins;
• and
• vanes each including a vane shroud fixed to the casing at a downstream side of the blade in an axial direction of the axis, of which at least a leading end portion formed upstream in the axial direction is located outside with respect to a first extended line of an inner peripheral surface of the casing in the radial direction about the axis, and a vane body extending inward from the vane shroud in the radial direction,
• wherein a leading edge of the vane body formed upstream in the axial direction includes:
• a receding start point;
• a radial outer end portion which is connected to the vane shroud and is receded downstream in the axial direction with respect to the receding start point;
• and a leading edge curved portion which is formed to connect the receding start point and the radial outer end portion and which is arched upstream in the axial direction, and
• wherein the receding start point is located outside a rear end of an inner surface of the blade shroud in the radial direction.