Patent ID: 9334745
Filing Date: 2016-05-10
CPC Classification: F01D,F05D

Claim Text:
1. A gas turbine stator vane, comprising: a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line of the vane; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion; wherein: an inner surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at a suction-surface side of the vane profile portion, a vertex of the inward convexed shape is positioned in a neighborhood of a leading edge of the vane profile portion, and a vertex of the outward convexed shape is positioned in a neighborhood of an intermediate region between the leading edge of the vane profile portion and a trailing edge thereof, an upstream end, in a direction of gas flow, of the inward convexed shape is positioned upstream of the leading edge, a line segment where radial positions of the inner surface of the outer-circumferential end wall at a cross section perpendicular to a rotating shaft of a turbine for the gas turbine stator vane are kept a constant value is positioned on the inward convexed shape of the outer-circumferential end wall inner surface, an area of the inward convexed shape of the outer-circumferential end wall inner surface in an axial direction of the turbine, starting upstream of the leading edge and ending downstream of the leading edge, having only the inward convexed shape and no outward convexed shapes, and a region where the outward convexed shape is formed has an area where the radial positions of the inner surface of the outer-circumferential end wall at a cross section perpendicular to the rotating shaft of the turbine are not kept a constant value.