US20150338101A1

US20150338101A1 - Turbomachine combustor including a combustor sleeve baffle

Info

Publication number: US20150338101A1
Application number: US14/283,681
Authority: US
Inventors: Nishant Govindbhai Parsania; Chandrasekhar Pushkaran
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2014-05-21
Filing date: 2014-05-21
Publication date: 2015-11-26
Also published as: CH709634A2; CN105091031A; JP2015222165A; DE102015107001A1

Abstract

A turbomachine combustor includes a combustor body extending from a head end to a discharge end. The combustor body includes a combustor liner defining a combustion chamber. A combustor sleeve surrounds the combustor liner. The combustor sleeve is spaced from the combustor liner forming a passage. The combustor sleeve includes at least one opening. A baffle is arranged in the passage. The baffle includes a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body. The baffle is configured and disposed to compress a fluid flow passing through the passage toward the head end.

Description

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a turbomachine combustor including a combustor sleeve baffle.
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. In some case, air for cooling is passed through a combustor sleeve that surrounds the combustor. The air for cooling may enter the combustor as part of the combustible mixture.

BRIEF DESCRIPTION OF THE INVENTION

According to an aspect of an exemplary embodiment, a turbomachine combustor includes a combustor body extending from a head end to a discharge end. The combustor body includes a combustor liner defining a combustion chamber. A combustor sleeve surrounds the combustor liner. The combustor sleeve is spaced from the combustor liner forming a passage. The combustor sleeve includes at least one opening. A baffle is arranged in the passage. The baffle includes a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body. The baffle is configured and disposed to compress a fluid flow passing through the passage toward the head end.
According to another aspect of an exemplary embodiment, a turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to the compressor portion and the turbine portion. The combustor assembly includes at least one combustor having a combustor body extending from a head end to a discharge end. The combustor body includes a combustor liner defining a combustion chamber. A combustor sleeve surrounds the combustor liner. The combustor sleeve is spaced from the combustor liner forming a passage. The combustor sleeve includes at least one opening. A baffle is arranged in the passage. The baffle includes a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body. The baffle is configured and disposed to compress a fluid flow passing through the passage toward the head end.
According to yet another aspect of an exemplary embodiment, a method of passing air through a combustor includes a passage defined between a combustor liner and a combustor sleeve including guiding a first airflow through the passage toward a head end of the combustor, passing the first airflow over a baffle, compressing the first airflow between the baffle and the combustor liner, introducing a second airflow into the first airflow downstream of the baffle, and merging the first airflow and the second airflow creating a substantially turbulent free airflow.
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 representation of a turbomachine system including a turbomachine having a combustor provided with a combustor sleeve baffle, in accordance with an exemplary embodiment;

FIG. 2 is a cross-sectional view of the combustor of FIG. 1;

FIG. 3 is a cross-sectional view of a portion of the combustor of FIG. 2;

FIG. 4 is a cross-sectional view of the baffle of FIG. 1;

FIG. 5 is a cross-sectional view of the baffle of FIG. 4 rotated circumferentially illustrating holes an a curvilinear surface of the baffle;

FIG. 6 is a partial perspective view of the baffle of FIG. 1; and

FIG. 7 is a cross-sectional view of the baffle, 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

With reference to FIGS. 1-4, a turbomachine system, in accordance with an exemplary embodiment, is indicated generally at 2, in FIG. 1. Turbomachine system 2 includes a turbomachine 3 having a compressor portion 4 operatively connected to a turbine portion 6 through a shaft 8. Compressor portion 4 is fluidically connected to turbine portion 6 through a combustor assembly 10 having at least one combustor 14. In the exemplary embodiment shown, turbomachine system 2 includes a driven load/component 20 operatively connected to turbomachine 3. Driven component 20 may take on a variety of forms including generators, pumps, and the load. Driven load may also take the form of a mode of transportation driven by turbomachine 3. Turbomachine system 2 is also shown to include an air intake system 24 fluidically connected to compressor portion 4.
Air enters air inlet system 24 and flows to compressor portion 4. The air is compressed and passed to combustor assembly 10. A portion of the air is passed into turbine portion 6 for cooling. In combustor assembly 10 the air is mixed with a fuel and or diluents to form a combustible mixture. The combustible mixture is combusted forming hot gases that pass from combustor assembly 10 to turbine portion 6. The hot gases expand through turbine portion 6 which converts thermal energy from the hot gases into mechanical energy that drives driven component 20. The hot gases pass from turbine portion 6 to an exhaust system (not shown).
As best shown in FIGS. 2-3, combustor 14 includes a combustor body 34 having a head end 36 and a discharge end 38 that is coupled to turbine portion 6 via a transition piece 42. Head end 36 houses a plurality of nozzles 46. Combustor 14 also includes a combustor liner 50 arranged within combustor body 34. Combustor liner 50 defines a combustion chamber 54. The combustible mixture is delivered into combustion chamber 54 and combusted to form the hot gases delivered to turbine portion 6 via transition piece 42. Combustor 14 also includes a combustor sleeve 60 that circumscribes combustor liner 50. Combustor sleeve 60 is spaced from combustor liner 50 forming a passage 64. Passage 64 delivers an airflow from compressor portion 4 along combustor liner 50 toward head end 36 of combustor 14. A plurality of openings, one of which is shown at 68, extend through, and circumferentially about, combustor sleeve 60. As will be detailed more fully below, openings 68 deliver an airflow into passage 64.
In accordance with an exemplary embodiment, combustor 14 includes a baffle 80 arranged in passage 64. Baffle 80 is arranged downstream from any obstacles that may be present in passage 64. With this arrangement, air passing over baffle 80 has a substantially unobstructed flow path to head end 36. As shown in FIG. 4, baffle 80 extends from a first end 83 coupled to combustor sleeve 60 to a second, cantilevered end 84 through a curvilinear surface 86. Curvilinear surface 86 extends across openings 68 and converges toward combustor liner 50. Air flowing through passage 64 downstream of baffle 80 may be turbulent and circumferentially and radially non-uniform as a result of interaction with various components such as injectors, cross-fire tubes, spark plugs, and the like such as shown at 88. The air reaches baffle 80 and is compressed between combustor liner 50 and curvilinear surface 86 reducing turbulence and/or reducing recirculation thereby enhancing circumferential uniformity. Additional air enters passage 64 through openings 68 and mixes with the air flowing across baffle 80. In accordance with an aspect of an exemplary embodiment, about 15% to about 30% of an overall airflow passing through passage 64 downstream of baffle 80 enters through openings 68. The addition of air through openings 68 further reduces turbulence in the airflow passing to head end 36. Reducing turbulence in the airflow passing to head end 36 enhances performance of combustor 14.
The reduction of turbulence in passage 64 resulting from compressing the air between combustion liner 50 and curvilinear surface 86 also improves heat transfer from a hot side of the combustion liner 50 to air passing over the combustion liner 50 thereby prolonging an overall service life and reliability of combustor assembly 10. Performance improvements may also be realized by a reduction in pressure losses and by a reduction of NOx emissions. More specifically, improving uniformity will lead to each nozzle 46 receiving a substantially identical (by volume) air flow and thus create a more uniform air/flow mixture for combustion. Uniformity of the air/fuel mixtures leads to more complete combustion and improved flameholding resulting in a reduction in emissions such as NOx.
In accordance with an aspect of an exemplary embodiment illustrated in FIG. 5, baffle 80 includes an opening 90 shown in the form of holes, two of which are shown at 93 and 94, formed in curvilinear surface 86. Holes 93 and 94 may be formed in curvilinear surface 86 between adjacent ones of openings 68. The incorporation of holes 93 and 94 enables additional air to flow through baffle 80 in areas in which openings 68 may not be present. In accordance with another aspect of an exemplary embodiment illustrated in FIG. 6, baffle 80 is shown to include an opening 98. Opening 98 takes the form of an interruption or discontinuity 100 in baffle 80. In a manner similar to that discussed above, opening 98 enables additional air to flow through baffle 80 in areas in which openings 68 may not be present.
At this point it should be understood that the exemplary embodiments describe a baffle arranged in an annular passage of a reverse flow combustor. The baffle conditions a turbulent airflow passing along the combustor toward the head end. More specifically, the baffle compresses the airflow against the combustor liner to reduce air recirculation leading to enhanced flow uniformity. In this manner, the exemplary embodiments reduce impingement pressure losses for air coming through openings in the baffle to enhance combustion properties of the combustor. It should also be understood that baffle 80 may include a divergent portion 160 that may further enhance flow uniformity in passage 64, as shown in FIG. 7. Divergent portion 160 may diverge from second end 84 at an angle of less than 5 degrees. Of course the angle of divergent portion 160 may also be greater than 5 degrees.
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 combustor comprising:

a combustor body extending from a head end to a discharge end, the combustor body including a combustor liner defining a combustion chamber;

a combustor sleeve surrounding the combustor liner, the combustor sleeve being spaced from the combustor liner forming a passage, the combustor sleeve including at least one opening; and

a baffle arranged in the passage, the baffle including a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body, the baffle being configured and disposed to compress a fluid flow passing through the passage toward the head end.

2. The turbomachine combustor according to claim 1, wherein the at least one opening comprises a plurality of openings extending circumferentially about the combustor sleeve.

3. The turbomachine combustor according to claim 2, wherein the baffle includes an opening arranged between adjacent ones of the plurality of openings.

4. The turbomachine combustor according to claim 3, wherein the opening includes at least one hole formed in the curvilinear surface.

5. The turbomachine combustor according to claim 1, wherein the baffle extends from a first end to a second, cantilevered end through the curvilinear surface, the second end includes a divergent portion.

6. The turbomachine combustor according to claim 5, wherein the divergent portion diverges from the second end at an angle of less than 5 degrees.

7. The turbomachine combustor according to claim 1, wherein the passage is substantially unobstructed downstream of the baffle.

8. A turbomachine comprising:

a compressor portion;

a turbine portion operatively connected to the compressor portion; and

a combustor assembly fluidically connected to the compressor portion and the turbine portion, the combustor assembly including at least one combustor, the at least one combustor including:

9. The turbomachine according to claim 8, wherein the at least one opening comprises a plurality of openings extending circumferentially about the combustor sleeve.

10. The turbomachine according to claim 9, wherein the baffle includes an opening arranged between adjacent ones of the plurality of openings.

11. The turbomachine according to claim 10, wherein the opening includes at least one hole formed in the curvilinear surface.

12. The turbomachine according to claim 8, wherein the baffle extends from a first end to a second, cantilevered end through the curvilinear surface, the second end includes a divergent portion.

13. The turbomachine according to claim 8, wherein the passage is substantially unobstructed downstream of the baffle.

14. A method of passing air through a combustor including a passage defined between a combustor liner and a combustor sleeve, the method comprising:

guiding a first airflow through the passage toward a head end of the combustor;

passing the first airflow over a baffle;

compressing the first airflow between the baffle and the combustor liner;

introducing a second airflow into the first airflow downstream of the baffle; and

merging the first airflow and the second airflow creating a substantially turbulent free airflow.

15. The method of claim 14, further comprising: passing a portion of the first airflow through the baffle.

16. The method of claim 15, wherein passing the portion of the first airflow through the baffle includes passing the portion of the first airflow through openings formed in the baffle.

17. The method of claim 15, wherein passing the portion of the first airflow through the baffle includes passing the portion of the first airflow through an interruption in the baffle.

18. The method of claim 14, further comprising: passing the substantially turbulent free airflow toward the head end of the combustor through an unobstructed portion of the passage.

19. The method of claim 14, wherein compressing the first airflow includes passing the first airflow over a curvilinear surface of the baffle.

20. The method of claim 14, further comprising: passing the second airflow over a divergent portion of the baffle.

21. The method of claim 14, wherein creating the substantially turbulent free airflow enhances heat transfer from the combustion liner.

22. The method of claim 14, wherein creating the substantially turbulent free airflow enhances circumferential uniformity of the airflow.

23. The method of claim 14, wherein creating the substantially turbulent free airflow reduces impingement pressure losses.