Strut cover for a turbine

Patent metadata

Field	Value
Publication number	US-11739658-B2
Application number	US-202017906357-A
Country	US
Kind code	B2
Filing date	Mar 20, 2020
Priority date	Mar 20, 2020
Publication date	Aug 29, 2023
Grant date	Aug 29, 2023

Abstract

A turbine operable to convey a flow of exhaust gas along a central axis includes a strut having a flow portion positioned within the flow of exhaust gas and a strut cover having a length and positioned to surround the flow portion of the strut, the strut cover including a leading-edge portion, a mid-chord portion, and a trailing-edge portion. The mid-chord portion has a uniform cross-section, and the trailing-edge portion has a trailing-edge center positioned such that the mid-chord portion and the trailing-edge portion define a master chord plane. The leading-edge portion defines a leading-edge nose, and the leading-edge portion is twisted with respect to the master chord plane and the leading-edge nose along the length defines a curve that is not coincident with the master chord plane.

First claim

What is claimed is:

1. A turbine operable to convey a flow of exhaust gas along a central axis, the turbine comprising:
a strut having a flow portion positioned within the flow of exhaust gas; and
a strut cover having a length and positioned to surround the flow portion of the strut, the strut cover including a leading-edge portion, a mid-chord portion, and a trailing-edge portion, the mid-chord portion having a uniform cross-section, and the trailing-edge portion having a trailing-edge center positioned such that the mid-chord portion and the trailing-edge portion are symmetric about a master chord plane, wherein the leading-edge portion defines a leading-edge nose, and wherein the leading-edge portion is twisted with respect to the master chord plane and the leading-edge nose along the length defines a curve that is not coincident with the master chord plane.

2. The turbine of claim 1 , further comprising an exhaust portion including an inner flow liner and an outer flow liner that cooperate to define an annular flow space, and wherein the flow portion is disposed within the annular flow space.

3. The turbine of claim 2 , wherein the strut cover is coupled to the inner flow liner and the outer flow liner, and the length extends between the inner flow liner and the outer flow liner.

4. The turbine of claim 3 , further comprising a first wall fillet formed between the inner flow liner and the strut cover and a second wall fillet formed between the outer flow liner and the strut cover.

5. The turbine of claim 1 , wherein the leading-edge portion includes a leading edge that extends the full length, and wherein the leading edge nose crosses the master chord plane at a single point.

6. The turbine of claim 5 , wherein a distance from the leading-edge center to the trailing-edge center measured parallel to the central axis is greater near the inner flow liner than near the outer flow liner.

7. The turbine of claim 1 , wherein the strut is the first of a plurality of struts and the strut cover is a first of a plurality of strut covers, and wherein each strut of the plurality of struts and each strut cover of the plurality of strut covers are circumferentially spaced apart from one another.

8. The turbine of claim 7 , wherein one of the strut covers of the plurality of strut covers is arranged at an oblique angle with respect to a radial axis of the turbine.

9. A turbine comprising:
an exhaust portion having an inner flow liner and an outer flow liner that cooperate to define an annular flow space, the annular flow space arranged to receive a flow in a flow direction; and
a strut cover positioned in the annular flow space and having a length normal to the flow direction between the inner flow liner and the outer flow liner, the strut cover including a uniform mid-chord portion that defines a master chord plane, a trailing-edge portion having a trailing-edge center that resides on the master chord plane, and a leading-edge portion having a leading-edge nose that is twisted with respect to the master chord plane such that the leading-edge nose crosses the master chord plane at a single point between the inner flow liner and the outer flow liner.

10. The turbine of claim 9 , wherein the strut cover is coupled to the inner flow liner and the outer flow liner, and wherein a first wall fillet is formed between the inner flow liner and the strut cover and a second wall fillet is formed between the outer flow liner and the strut cover.

11. The turbine of claim 9 , wherein the master chord plane is a radial plane that includes a central axis of the turbine.

12. The turbine of claim 9 , wherein a distance from the leading-edge nose to the trailing-edge center measured parallel to the flow direction is greater near the inner flow liner than near the outer flow liner.

13. The turbine of claim 9 , wherein the strut cover is a first of a plurality of strut covers, and wherein each strut cover of the plurality of strut covers are circumferentially spaced apart from one another.

14. The turbine of claim 13 , wherein one of the strut covers of the plurality of strut covers is arranged at an oblique angle with respect to a radial axis of the turbine.

15. A turbine comprising:
an exhaust portion having an inner flow liner and an outer flow liner that cooperate to define an annular flow space;
a strut having a flow portion positioned in the annular flow space and extending along an axis between the inner flow liner and the outer flow liner; and
a strut cover positioned in the annular flow space and extending between the inner flow liner and the outer flow liner, the strut cover surrounding the flow portion and including a leading-edge portion, a mid-chord portion, and a trailing-edge portion that cooperate to define a plurality of cross-sections normal to the axis, and wherein each cross-section defines a camber line and wherein the camber lines overlay one another in the mid-chord portion and the trailing-edge portion and the camber lines do not overlay one another in the leading-edge portion.

16. The turbine of claim 15 , wherein the strut cover is coupled to the inner flow liner and the outer flow liner, and wherein a first wall fillet is formed between the inner flow liner and the strut cover and a second wall fillet is formed between the outer flow liner and the strut cover.

17. The turbine of claim 15 , wherein each of the plurality of cross-sections includes a leading-edge center and a trailing-edge center and defines a length measured from the leading-edge center to the trailing-edge center, and wherein the length is not uniform in the plurality of cross-sections.

18. The turbine of claim 17 , wherein the trailing-edge portion of each of the plurality of cross-sections cooperate to define a tapered trailing-edge portion.

19. The turbine of claim 15 , wherein the strut cover is a first of a plurality of strut covers, and wherein each strut cover of the plurality of strut covers are circumferentially spaced apart from one another, and wherein the spacing is unequal.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Flitan Horia
• Taremi Farzad
• Wong Li Shing
• Gustafson Ross

Classifications

• F01D25/162 Primary

  Bearing supports · CPC title

• F01D9/04

  forming ring or sector · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/50

  Bearings · CPC title

• F05D2250/72

  symmetric · CPC title