Gas turbine stator vane

Patent metadata

Field	Value
Publication number	US-9334745-B2
Application number	US-201213455612-A
Country	US
Kind code	B2
Filing date	Apr 25, 2012
Priority date	Apr 28, 2011
Publication date	May 10, 2016
Grant date	May 10, 2016

Abstract

A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes 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; 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. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

First claim

What is claimed is:

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.

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

3. The gas turbine stator vane according to claim 1 , wherein:
an outer surface of the inner-circumferential end wall that is an outer circumferential surface of the inner-circumferential end wall has an outward convexed shape and an inward convexed shape, at the suction surface side of the vane profile portion;
a vertex of an outward convexed shape on the outer surface of the inner-circumferential end wall is positioned in the neighborhood of the leading edge of the vane profile portion; and
a vertex of an inward convexed shape on the outer surface of the inner-circumferential end wall is positioned in the neighborhood of the intermediate region between the leading edge and the trailing edge of the vane profile portion.

4. The gas turbine stator vane according to claim 3 , wherein:
if a contact point between the end wall and the leading edge of the vane profile portion is represented as existing at a position of 0%, and also a contact point between the end wall and the trailing edge of the vane profile portion is represented as existing at a position of 100% on a straight line passing through the two contact points, then the neighborhood of the leading edge is defined by a range of less than or equal to 40% of the straight line.

5. The gas turbine stator vane according to claim 3 , wherein:
if a contact point between the end wall and the leading edge of the vane profile portion is represented as existing at a position of 0%, and also a contact point between the end wall and the trailing edge of the vane profile portion is represented as existing at a position of 100% on a straight line passing through the two contact points, then the neighborhood of the intermediate region is defined by a range from 30% to 80% of the straight line.

Assignees

• Miyoshi Ichiro
• Higuchi Shinichi
• Noda Masami
• Mitsubishi Hitachi Power Sys

Inventors

• Miyoshi Ichiro
• Higuchi Shinichi
• Noda Masami

Classifications

• F05D2250/184

  sinusoidal · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F05D2240/10

  Stators · CPC title

• F05D2250/711

  convex · CPC title