US20150192020A1

US20150192020A1 - Turbomachine including a component having a trench

Info

Publication number: US20150192020A1
Application number: US14/150,190
Authority: US
Inventors: Anshuman Singh; Joe Timothy BROWN; Ravi Meenaksh; Ibrahim Sezer
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2014-01-08
Filing date: 2014-01-08
Publication date: 2015-07-09

Abstract

A turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a shroud mounted in one of the compressor portion and the turbine portion. The shroud includes a radial outer side, and a plurality of side surfaces. The radial outer side includes a recessed portion. A trench is formed in the recessed portion, and a cooling passage extends between the trench and at least one of the plurality of side surfaces. An airfoil component is arranged in the one of the compressor portion and the turbine portion. The airfoil component includes an airfoil portion having at least one mounting member. The at least one mounting member includes an internal cavity. A trench element is formed in the internal cavity, and a cooling passage element extends between the trench element and an external surface of the nozzle.

Description

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to the art of turbomachines and, more particularly to a turbomachine including a component having a trench.
Turbomachines include a compressor portion linked to a turbine portion through a common compressor/turbine shaft and a combustor assembly. An inlet airflow is passed through an air intake toward the compressor portion. In the compressor portion, the inlet airflow is compressed through a number of sequential stages toward the combustor assembly. In the combustor assembly, the compressed airflow mixes with a fuel to form a combustible mixture. The combustible mixture is combusted in the combustor assembly to form hot gases. The hot gases are guided along a hot gas path of the turbine portion through a transition piece. The hot gases expand along a hot gas path through a number of turbine stages acting upon turbine bucket airfoils mounted on wheels to create work that is output, for example, to power a generator. A portion of the compressed air is passed through various components of the turbomachine for cooling purposes.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect of an exemplary embodiment, a turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a shroud mounted in one of the compressor portion and the turbine portion. The shroud includes a radial inner side, a radial outer side arranged opposite the radial inner side, and a plurality of side surfaces joining the radial inner side and the radial outer side. The radial outer side includes a recessed portion. At least one trench is formed in the recessed portion, and at least one cooling passage extends between the at least one trench and at least one of the plurality of side surfaces. An airfoil component is arranged in the one of the compressor portion and the turbine portion. The airfoil component includes an airfoil portion having at least one mounting member including an internal cavity and a plurality of side surface portions. At least one trench element is formed in the internal cavity, and at least one cooling passage element extends between the at least one trench element and one of the plurality of side surface portions.
According to another aspect of an exemplary embodiment, a turbomachine shroud includes a radial inner side, and a radial outer side arranged opposite the radial inner side. The radial outer side includes a recessed portion. A plurality of side surfaces joins the radial inner side and the radial outer side. At least one trench is formed in the recessed portion, and at least one cooling passage extends between the at least one trench and at least one of the plurality of side surfaces.
According to yet another aspect of an exemplary embodiment, a turbomachine airfoil component includes an airfoil portion having at least one mounting member including an internal cavity and a plurality of side surface portions. At least one trench element is formed in the internal cavity, and at least one cooling passage element extends between the at least one trench element and one of the plurality of side surface portions.
According to still yet another aspect of an exemplary embodiment, a turbomachine component includes a plurality of surfaces that define an internal cavity, at least one trench formed in the internal cavity, and at least one cooling passage extending between the at least one trench and at least one of the plurality of surfaces.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF DRAWINGS

The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:

FIG. 1 is a schematic view of a turbomachine including a component having a trench, in accordance with an exemplary embodiment;

FIG. 2 is a partial cross-sectional view of a turbine section of the turbomachine of FIG. 1 depicting a turbomachine shroud including a trench and a turbomachine airfoil component including a trench, in accordance with an exemplary embodiment;

FIG. 3 is a perspective view of an inner casing of the turbine portion supporting the turbomachine shroud of FIG. 2;

FIG. 4 is a perspective view of the turbomachine shroud of FIG. 3;

FIG. 5 is a plan view of a radial outer surface of the turbomachine shroud of FIG. 4;

FIG. 6 is a detailed view of the radial outer surface of the turbomachine shroud of FIG. 5 illustrating a trench, in accordance with an exemplary embodiment;

FIG. 7 is a perspective view of the turbomachine airfoil component of FIG. 2 shown in the form of a nozzle;

FIG. 8 is a partially cut-away view of a first mounting member of the nozzle of FIG. 7, in accordance with an aspect of an exemplary embodiment;

FIG. 9 is a cut-away side view of the first mounting member of FIG. 8; and

FIG. 10 is a partially cut-away view of a first mounting member of the nozzle of FIG. 7, in accordance with another aspect of an exemplary embodiment.

The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.

DETAILED DESCRIPTION OF THE INVENTION

A turbomachine, in accordance with an exemplary embodiment, is illustrated generally at 2, in FIG. 1. Turbomachine 2 includes a compressor portion 4 fluidically connected to a turbine portion 6 through a combustor assembly 8. Combustor assembly 8 may include a plurality of combustors, one of which is indicated at 10. Compressor portion 4 may also be mechanically linked to turbine portion 6 through a common compressor/turbine shaft 12. Compressor portion 4 includes an outer casing 16 that supports a first plurality of airfoil components or compressor vanes/nozzles, one of which is indicated at 18. Outer casing 16 also supports a plurality of compressor shrouds, one of which is indicated at 20. Compressor portion 4 also includes a plurality of stages (not separately labeled) each having another plurality of airfoil components or compressor buckets/blades, one of which is indicated at 22, operatively connected to shaft 12. Compressor blades 22 include a mounting member or platform (not separately labeled) that interfaces with a compressor wheel (also not separately labeled) and rotate within outer casing 16.
Turbine portion 6 includes an outer casing 30 that supports a plurality of inner casing members, one of which is shown at 32 in FIG. 2. Turbine portion 6 includes a first plurality of airfoil components or turbine nozzles, one of which is shown at 36, fixedly mounted relative to outer casing 30. Turbine portion 6 also includes a plurality of turbine shrouds 38. Each turbine shroud 38 is supported by a corresponding inner casing member 32. Further, turbine portion 6 includes a plurality of turbine stages (not separately labeled) each having another plurality of airfoil components or turbine buckets/blades, one of which is indicated at 40. Turbine blades 40 include a mounting member or platform 41 that interfaces with a turbine wheel 43.
Air passes into compressor portion 4 and is compressed through the compressor stages (not separately labeled) forming compressed air. A portion of the compressed air passes to turbine portion 6 for cooling. For example, cooling air is passed to each inner casing member 32 and directed onto each turbine shroud 38. Cooling air is also passed into each turbine nozzle 36. Another portion of the compressed air is passed to combustor assembly 8 and mixed with a fuel to form a combustible mixture. The combustible mixture is combusted in each combustor 10 forming hot gases. The hot gases flow into turbine portion 6 through a transition piece (not separately labeled). The hot gases expand through turbine portion 6 creating work that may be used to drive a generator, a pump, or provide power to a motor vehicle such as an airplane or locomotive.
As shown in FIG. 3, inner casing member 32 includes a body 46 having a casing support portion 48 and a shroud support portion 50. Casing support portion 48 affixes inner casing member 32 relative to outer casing 30. Shroud support portion 50 includes a first hook 51 and a second hook 52. First and second hooks 51 and 52 operatively connect turbine shroud 38 to inner casing member 32. An impingement box 57 is arranged between inner casing member 32 and turbine shroud 38. Impingement box 57 distributes cooling air passing through inner casing member 32 onto turbine shroud 38.
Reference will now follow to FIGS. 4-5 in describing turbine shroud 38. Turbine shroud 38 includes a radial inner surface 70 and a radial outer surface 72. Radial outer surface 72 forms part of a recessed portion 74 referred to by those skilled in the art as the “bathtub” that establishes an internal cavity (not separately labeled) of turbine shroud 38. Turbine shroud 38 also includes an upstream side surface 79, a downstream side surface 81, a first circumferential side surface 84 and a second, opposing circumferential side surface 86. In the exemplary embodiment shown, a rib 94 extends between first and second circumferential side surfaces 84 and 86 dividing recessed portion 74 into an upstream portion 96 and a downstream portion 98.
In accordance with an exemplary embodiment, turbine shroud 38 includes a plurality of trenches formed in recessed portion 74. More specifically, turbine shroud 38 includes a first trench 108, a second trench 109, a third trench 110, and a fourth trench 111. First trench 108 extends along first circumferential side surface 84 in upstream portion 96. Second trench 109 extends along first circumferential side surface 84 in downstream portion 98. Conversely, third trench 110 extends along second circumferential side surface 86 in upstream portion 96, and fourth trench 111 extends along second circumferential side surface 86 in downstream portion 98.
A first plurality of cooling passages 115 extends from first trench 108 to first circumferential side surface 84 and a second plurality of cooling passages 116 extend from second trench 109 to first circumferential side surface 84. A third plurality of cooling passages 117 extends from third trench 110 to second circumferential side surface 86 and a fourth plurality of cooling passages 118 extends from fourth trench 110 to second circumferential side surface 86. Cooling passages 115, 116, 117, and 118 provide an outlet for cooling air passing from inner casing member 32 into recessed portion 74 to cool radial inner surface 70. At this point it should be understood that turbine shroud 38 may include a first trench 108 that extends continuously along first circumferential side surface 84 and a second trench 109 that extends continuously along second circumferential side surface 86. It should also be understood that turbine shroud 38 may include a single trench that extends along one or the other of first or second circumferential side surfaces 84 or 86, or a single trench in one or more of upstream portion 96 or downstream portion 98. The particular number and location of trenches may vary.
Reference will now follow to FIG. 6, in describing first trench 108 with an understanding that the remaining trenches 109-111 include similar structure. First trench 108 includes a bottom surface section 132, an upstream side surface section 134, and a downstream side surface section 135. First trench 108 also includes a first circumferential side section 137 and a second circumferential side surface section 138 that extend between upstream side surface section 134 and downstream side surface section 135. Cooling passages 115 extend from first circumferential side surface 137 to first circumferential side surface 84. The trenches provide machining access for cooling passages 115 which may reduce temperatures at first and/or second circumferential side surfaces 84 and 86 to enhance component life and reduce maintenance costs.
Reference will now follow to FIGS. 7-9 in describing airfoil component or turbine nozzle 36, in accordance with an aspect of an exemplary embodiment. Turbine nozzle 36 includes an airfoil portion 160 extending from a first, radial outer end 162 to a second, radial inner end 163. A first side wall or mounting member 170 is provided at first, radial outer end 162 and a second side wall or mounting member 174 is provided at second, radial inner end 163. First mounting member 170 supports turbine nozzle 36 relative to outer casing 30. Second mounting member 174 also supports turbine nozzle 36 and provides a sealing surface 175 (FIG. 2) that substantially, fluidically isolates a hot gas path (not separately labeled) from a wheel space (also not separately labeled) of turbine portion 6. First mounting member 170 includes a plurality of side surface portions 172 including an upstream end 178, a downstream end 180, a first circumferential side portion 181 and a second circumferential side portion 182. First mounting member 170 also includes a first internal cavity 184. Second mounting member 174 also includes a plurality of side surface portions 185 including an upstream end 186, a downstream end 188, a first circumferential side surface 190 and a second circumferential side surface 192. Second mounting member 174 also includes a second internal cavity 192
In accordance with an aspect of an exemplary embodiment, a trench 194 extends across downstream end portion 180 of internal cavity 184 of first mounting member 170. Trench 194 fluidically connects with a first plurality of cooling passages 196. Cooling passages 196 guide cooling air from first internal cavity 184 through downstream end 180 into hot gases flowing along a hot gas path (not separately labeled) of turbine portion 6 via downstream end 180. Of course, it should be understood that cooling passages may pass through others of the side surface portions of internal cavity 184 of first mounting member 170. It should also be understood that trenches may extend along another of the side surface portion and need not be located at the downstream end.
Similarly, internal cavity 192 of second mounting member 174 includes a trench 197 that extends across downstream end portion 188 and fluidically connects with a second plurality of cooling passages 198. Cooling passages 198 guide cooling air from second internal cavity 192 into hot gases flowing along the hot gas path via downstream end portion 188. Of course, in a manner also similar to that discussed above, it should be understood that cooling passages may pass through others of the side surface portions of internal cavity 192 of second mounting member 174. It should also be understood that trenches may extend along another of the side surface portion and need not be located at the downstream end. Further, it should be understood, that in lieu of a continuous trench, a plurality of trenches or depressions 200 may be formed in first internal cavity 184 such as shown in FIG. 10. The plurality of trenches 200 may connect with corresponding ones of cooling passages 196. Of course it should be understood that internal cavity 192 of second mounting member 174 may also be formed with a plurality of trenches.
At this point it should be understood that the trenches formed in the turbine nozzle provide machining access for forming the cooling passages that pass through portions of first and/or second mounting members to facilitate more uniform cooling thereby increasing component life and reducing maintenance costs. It should also be understood that while the exemplary embodiments are described in terms of a turbine shroud and a turbine nozzle, the trenches may be formed in other turbine components. Further, it should be understood that trenches may be formed in other airfoil components such as platform portions of compressor and/or turbine blades. Further, trenches may be formed in components provided in the compressor portion to enhance cooling or direct fluid through portions of a component that might otherwise be too thin to include passages.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims

What is claimed is:

1. A turbomachine comprising:

a compressor portion;

a turbine portion operatively connected to the compressor portion;

a shroud mounted in one of the compressor portion and the turbine portion, the shroud including a radial inner side, a radial outer side arranged opposite the radial inner side, and a plurality of side surfaces joining the radial inner side and the radial outer side, the radial outer side including a recessed portion;

at least one trench formed in the recessed portion;

at least one cooling passage extending between the at least one trench and at least one of the plurality of side surfaces;

an airfoil component arranged in the one of the compressor portion or the turbine portion, the airfoil component including an airfoil portion having at least one mounting member, including an internal cavity, the at least one mounting member including a plurality of side surface portions;

at least one trench element formed in the internal cavity; and

at least one cooling passage element extending between the at least one trench element and the one of the plurality of side surface portions.

2. The turbomachine according to claim 1, wherein the plurality of side surfaces includes an upstream side surface, a downstream side surface, a first circumferential side surface and a second circumferential side surface, the plurality of cooling passages extending from the at least one trench to at least one of the first and second circumferential side surfaces.

3. The turbomachine according to claim 2, wherein the at least one trench includes a first trench extending along the first circumferential side surface and a second trench extending along the second circumferential side surface, wherein, the plurality of cooling passages includes a first plurality of cooling passages extending between the first trench and the first circumferential side surface and a second plurality of cooling passages extending between the second trench and the second circumferential side surface.

4. The turbomachine according to claim 1, wherein the shroud is mounted in a turbine portion of a turbomachine.

5. The turbomachine according to claim 1, wherein the plurality of side surface portions include an upstream end, a downstream end, a first circumferential side portion and a second circumferential side portion, the at least one trench being formed at the downstream end of the at least one mounting member.

6. The turbomachine according to claim 1, wherein the airfoil component comprises a nozzle including a first mounting member having a downstream end and a second mounting member having a downstream end, the first mounting member including a first internal cavity having first trench and the second mounting member including a second internal cavity having a second trench, the first trench being formed at the downstream end of the first mounting member and the second trench being formed at the downstream end of the second mounting member.

7. The turbomachine according to claim 1, wherein the at least one cooling passage comprises a plurality of cooling passages extending from the at least one trench to the one of the plurality of side surface portions.

8. The turbomachine according to claim 1, wherein the at least one trench includes a plurality of trenches extending along the one of the plurality of side surface portions.

9. A turbomachine shroud comprising:

a radial inner side;

a radial outer side arranged opposite the radial inner side, the radial outer side including a recessed portion;

a plurality of side surfaces joining the radial inner side and the radial outer side;

at least one trench formed in the recessed portion; and

at least one cooling passage extending between the at least one trench and at least one of the plurality of side surfaces.

10. The turbomachine shroud according to claim 9, wherein the plurality of side surfaces includes an upstream side surface, a downstream side surface, a first circumferential side surface and a second circumferential side surface, the plurality of cooling passages extending from the at least one trench to at least one of the first and second circumferential side surfaces.

11. The turbomachine shroud according to claim 9, wherein the at least one trench includes a first trench extending along one of the plurality of side surfaces and a second trench extending along another of the plurality of side surfaces, wherein, the plurality of cooling passages includes a first plurality of cooling passages extending between the first trench and the one of the plurality of sides surfaces and a second plurality of cooling passages extending between the second trench and the other of the plurality of side surfaces.

12. The turbomachine shroud according to claim 9, wherein the radial outer side includes a plurality of recessed portions.

13. The turbomachine shroud according to claim 12, wherein the at least one trench includes a first trench arranged along one of the opposing ones of the plurality of side surfaces and a second trench arranged along another of the opposing ones of the plurality of side surfaces, the first and second trenches being arranged in the upstream end portion.

14. The turbomachine shroud according to claim 12, wherein the at least one trench includes a first trench arranged along one of the opposing ones of the plurality of side surfaces and a second trench arranged along another of the opposing ones of the plurality of side surfaces, the first and second trenches being arranged in the downstream end portion.

15. The turbomachine shroud according to claim 12, wherein the at least one trench includes a first trench arranged along one of the opposing ones of the plurality of side surfaces and a second trench arranged along another the opposing ones of the plurality of side surfaces in the upstream end portion and a third trench arranged along the one of the opposing ones of the plurality of side surfaces and fourth trench arranged along the another of the opposing ones of the plurality of side surfaces in the downstream end portion.

16. A turbomachine airfoil component comprising:

an airfoil portion having at least one mounting member including an internal cavity, the at least one mounting member including a plurality of side surface portions;

at least one trench element formed in the internal cavity; and

at least one cooling passage element extending between the at least one trench element and one of the plurality of side surface portions.

17. The turbomachine nozzle according to claim 16, wherein the plurality of side surface portions includes an upstream end, a downstream end, a first circumferential side portion and a second circumferential side portion, the at least one trench being formed at the downstream end of the at least one mounting member.

18. The turbomachine nozzle according to claim 16, wherein the airfoil component comprises a nozzle including a first mounting member having a downstream end and a second mounting member having a downstream end, the first mounting member including a first internal cavity having first trench and the second mounting member including a second internal cavity having a second trench, the first trench being formed at the downstream end of the first mounting member and the second trench being formed at the downstream end of the second mounting member.

19. The turbomachine nozzle according to claim 16, wherein the at least one cooling passage element comprises a plurality of cooling passages extending from the at least one trench to the one of the plurality of side surface portions.

20. The turbomachine nozzle according to claim 17, wherein the at least one trench includes a plurality of trenches extending along the one of the plurality of side surface portions.

21. A turbomachine component comprising:

a plurality of surfaces that define an internal cavity;

at least one trench formed in the internal cavity; and

at least one cooling passage extending between the at least one trench and at least one of the plurality of surfaces.

22. The turbomachine component according to claim 21, wherein the plurality of surfaces includes a first circumferential side surface and a second circumferential side surface, the at last one trench extending along one of the first and second circumferential side surfaces.

23. The turbomachine component according to claim 22, wherein the at least one cooling passage extends from the at least one trench to the at least one of the first and second circumferential side surfaces.

24. The turbomachine component according to claim 22, wherein the plurality of surfaces includes an upstream side surface, and a downstream side surface, the at least one trench extending along one of the upstream side surface and the downstream side surface.

25. The turbomachine component according to claim 24, wherein the at least one trench extends along the downstream side surface.

26. The turbomachine component according to claim 25, wherein the at least one cooling passage extends between the at least one trench and the downstream side surface.