Gas turbine including a contoured end wall section of a rotor blade

Patent metadata

Field	Value
Publication number	US-10012087-B2
Application number	US-201214413826-A
Country	US
Kind code	B2
Filing date	Sep 12, 2012
Priority date	Sep 12, 2012
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade. In a gas turbine rotor blade 4 including a wing shape section 12 formed of a negative pressure surface 12 d extending from a front edge 12 a to a rear edge 12 b , a pressure surface 12 c opposing the negative pressure surface 12 d and extending from the front edge 12 a to the rear edge 12 b , and a tip surface 13 surrounded by the top end of the negative pressure surface 12 d and the top end of the pressure surface 12 c , and an end wall section 10 connected to the bottom end of the negative pressure surface 12 d and the bottom end of the pressure surface 12 c , the rotor blade has a convex shape in positions constituting the negative pressure surface 12 d side and the front edge 12 a side of the end wall section 10 , and the rotor blade has a concave shape in positions constituting the pressure surface 12 c side and the front edge 12 a side of the end wall section 10.

First claim

The invention claimed is:

1. A gas turbine rotor blade, comprising:
a wing shape section formed of a negative pressure surface that extends from a front edge to a rear edge, a pressure surface that opposes the negative pressure surface and extends from the front edge to the rear edge, and a tip surface surrounded by a top end of the negative pressure surface and a top end of the pressure surface; and
an end wall section that is connected to a bottom end of the negative pressure surface and a bottom end of the pressure surface, wherein
the gas turbine rotor blade has a convex shape at a joint between the negative pressure surface of the wing shape section and a front edge side of the end wall section, and the gas turbine rotor blade has a concave shape at a joint between the pressure surface of the wing shape section and the front edge side of the end wall section.

2. The gas turbine rotor blade according to claim 1 , wherein
the gas turbine rotor blade has a convex shape at a position constituting a rear edge side of the concave shape.

3. A gas turbine of an open cooling system, comprising:
a compressor that compresses air;
a combustor that combusts air compressed by the compressor and fuel and forms a combustion gas; and
a turbine driven by the combustion gas formed by the combustor,
with the turbine including a plurality of rotor blades that receive the combustion gas and rotate and a plurality of stationary blades that restore static pressure of the combustion gas that has rotated the rotor blades, and emitting air after cooling having cooled a high temperature portion to a mainstream, wherein
at least one of the rotor blades includes a wing shape section formed of a negative pressure surface extending from a front edge to a rear edge, a pressure surface opposing the negative pressure surface and extending from the front edge to the rear edge, a tip surface surrounded by both a top end of the negative pressure surface and a top end of the pressure surface opposing the negative pressure surface, and an end wall section connected to a bottom end of the negative pressure surface;
the at least one of the rotor blades has a convex shape at a joint between the negative pressure surface of the wing shape section and a front edge side of the end wall section between the plurality of rotor blades; and
the at least one of the rotor blades has a concave shape at a joint between the pressure surface of the wing shape section and the front edge side of the end wall section between the plurality of rotor blades.

4. The gas turbine according to claim 3 , wherein
the at least one of the rotor blades has a convex shape on a rear edge side of the concave shape.

5. The gas turbine rotor blade according to claim 1 , wherein
when a position of an intersection point of the front edge and the end wall section is made 0% and a position of an intersection point of the rear edge and the end wall section is made 100%, a vertex of the convex shape is positioned within a range of 40% or less on the negative pressure surface.

6. The gas turbine rotor blade according to claim 1 , wherein
when a position of an intersection point of the front edge and the end wall section is made 0% and a position of an intersection point of the rear edge and the end wall section is made 100%, a vertex of the concave shape is positioned within a range of 40% or less on the pressure surface.

7. The gas turbine rotor blade according to claim 2 , wherein
when a position of a contact point of the front edge and the end wall section is made 0% and a position of a contact point of the rear edge and the end wall section is made 100%, a vertex of the convex shape is positioned within a range of 30% or more and 80% or less on the pressure surface.

8. The gas turbine according to claim 3 , further comprising a seal mechanism that restricts a flow rate of a cooling refrigerant passing through a gap between a rotating body and a stationary body.

9. A method for operating a gas turbine of an open cooling system according to claim 3 , comprising:
producing a flow of the combustion gas formed by the combustor; and
rectifying the flow of the combustion gas utilizing a flow of a mainstream of the combustion gas by using rotor blades of shapes leading the combustion gas flowing in a vicinity of the end wall section.

10. The gas turbine according to claim 3 , wherein
when a position of an intersection point of the front edge and the end wall section is made 0% and a position of an intersection point of the rear edge and the end wall section is made 100%, a vertex of the convex shape is positioned within a range of 40% or less on the negative pressure surface and front edge side of the end wall section.

11. The gas turbine according to claim 3 , wherein
when a position of an intersection point of the front edge and the end wall section is made 0% and a position of an intersection point of the rear edge and the end wall section is made 100%, a vertex of the concave shape is positioned within a range of 40% or less on the pressure surface and front edge side of the end wall section.

12. The gas turbine according to claim 4 , wherein
when a position of a contact point of the front edge and the end wall section is made 0% and a position of a contact point of the rear edge and the end wall section is made 100%, a vertex of the convex shape is positioned within a range of 30% or more and 80% or less on the pressure surface and front edge side of the end wall section.

Assignees

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

Inventors

• Miyoshi Ichiro
• Higuchi Shinichi
• Noda Masami

Classifications

• F01D5/187

  Convection cooling · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F05D2240/55

  Seals · CPC title

• F01D5/143 Primary

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

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title