Staggered double row, slotted airfoil design for gas turbine exhaust frame

Patent metadata

Field	Value
Publication number	US-9422864-B2
Application number	US-201213723047-A
Country	US
Kind code	B2
Filing date	Dec 20, 2012
Priority date	Dec 20, 2012
Publication date	Aug 23, 2016
Grant date	Aug 23, 2016

Abstract

A gas turbine exhaust frame includes an inner barrel and an outer barrel establishing an annular exhaust gas flow path therebetween. A plurality of airfoils extend radially between the inner barrel and the radially, outer barrel, the plurality of struts arranged in first and second axially-spaced and circumferentially-staggered rows.

First claim

What is claimed is:

1. A gas turbine exhaust frame an inner substantially cylindrical wall;
an inner wall which is substantially circular in cross section;
an outer wall which is substantially circular in cross section and the outer wall tapers radially outwardly along a direction of exhaust gas flow from a gas turbine;
an annular exhaust gas flow path defined between the inner wall and outer wall, and
a plurality of airfoils extending radially between said inner wall and said outer wall, said plurality of airfoils arranged in first and second axially-spaced, circumferentially-staggered rows,
wherein the airfoils in said second axially-spaced, circumferentially-staggered row at least partially overlap in an axial direction of the exhaust frame with airfoils in said first axially-spaced, circumferentially-staggered row,
wherein each of said plurality of airfoils comprises an airfoil portion including a leading edge and a trailing edge; a root end attached to the inner wall and a tip end attached to the outer wall, and
wherein one or more of said airfoils is provided with a radially-extending slot having an inlet along and adjacent at least a portion of said leading edge on one side of said airfoil.

2. The gas turbine exhaust frame according to claim 1 wherein the one or more of said airfoils provided with the radially-extending slot is in the front row.

3. The gas turbine exhaust frame according to claim 1 wherein the one or more of said airfoils provided with the radially-extending slot are in the first and second rows.

4. The gas turbine exhaust frame according to claim 1 wherein said radially-extending slot has an outlet on an opposite side of said airfoil closer to said trailing edge.

5. A gas turbine exhaust diffuser comprising:
a frame having an inner wall and an outer wall defining an annular exhaust gas flow channel, wherein the inner wall and outer wall are each substantially circular in cross section; and
a plurality of airfoils extending between said inner and outer walls, said plurality of airfoils arranged in first and second axially-spaced, circumferentially-staggered rows, wherein said first and second axially-spaced, circumferentially-staggered rows at least partially overlap in an axial direction,
wherein one or more of said airfoils is provided with a slot having an inlet extending radially along and adjacent at least a portion of a leading edge of one side of said one or more airfoils.

6. The gas turbine exhaust diffuser according to claim 5 wherein each of said airfoils in said first row is provided with a slot having an inlet extending radially along and adjacent at least a portion of said leading edge on one side of said airfoil.

7. The gas turbine exhaust diffuser according to claim 5 wherein each of said airfoils in said first and second rows is provided with a slot having an inlet extending radially along and adjacent at least a portion of a respective leading edge.

8. The gas turbine exhaust diffuser according to claim 7 wherein each slot is oriented at an acute angle relative to a longitudinal center axis of said inner wall, and extends from an inlet on one side of said airfoil to an outlet on an opposite side of said airfoil.

9. The gas turbine exhaust diffuser of claim 8 wherein said first and second axially-spaced, circumferentially-staggered rows overlap by about 50%.

10. A gas turbine exhaust diffuser comprising:
a frame having an inner wall and an outer wall defining an annular exhaust gas flow channel, wherein the inner wall and outer walls each have substantially circular cross sections;
a plurality of airfoils extending between said inner and outer walls, said plurality of airfoils arranged in first and second annular, axially-spaced, and circumferentially-staggered rows;
each of said plurality of airfoils having a leading edge and a trailing edge and a slot extending radially along and adjacent at least a portion of said leading edge, said slot having an inlet on one side of said airfoil extending angularly in a downstream direction to an outlet on an opposite side of said airfoil.

11. The gas turbine exhaust diffuser according to claim 10 wherein each slot is angled to substantially match a swirl angle of gas flow entering the diffuser.

12. The gas turbine exhaust diffuser according to claim 11 wherein each slot is oriented at an acute angle relative to a longitudinal center axis of said inner wall.

13. The gas turbine exhaust diffuser according to claim 11 said first and second axially-spaced, circumferentially-staggered rows at least partially overlap in an axial direction.

14. The gas turbine exhaust diffuser according to claim 13 wherein said first and second axially-spaced, circumferentially-staggered rows overlap in said axial direction by about 50%.

Assignees

• Gen Electric

Inventors

• Sakekar Kunal Upendra
• Subramaniyan Moorthi
• Pakkala Srinivasarao

Classifications

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F01D9/041

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