Patent ID: 11867090
Assignee: IHI CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. An assembly comprising a plurality of stator vanes provided rearward of a plurality of rotor blades, a stator vane of the plurality of stator vanes comprising:
an airfoil body having an airfoil cross section, wherein
a maximum airfoil thickness position of the airfoil body in the airfoil cross section satisfies following conditions at least on a tip side of the airfoil body:
(a) on a plane expanded in a circumferential direction in which the plurality of stator vanes are arranged, the maximum airfoil thickness position is located in a region between a trailing edge of the airfoil body and an intersection of the airfoil body, wherein the intersection is between the airfoil body and a line which is parallel to an extension line of a camber line of a rotor blade of the plurality of rotor blades at a trailing edge of the rotor blade of the plurality of rotor blades, the extension line also passes through a leading edge of a circumferentially adjacent stator vane of the plurality of stator vanes, and
(b) the maximum airfoil thickness position is located in a region between a position of a chord ratio 0.2 and a chord ratio 0.8, and
the chord ratio is a value obtained by dividing a distance from the leading edge of the airfoil body to a position on a chord of the airfoil body by a full length of the airfoil body chord.