US20140238034A1

US20140238034A1 - Turbomachine combustor assembly and method of operating a turbomachine

Info

Publication number: US20140238034A1
Application number: US13/983,878
Authority: US
Inventors: Ilya Aleksandrovich Slobodyanskiy; Sergey Aleksandrovich Stryapunin; Dmitry Vladlenovich Tretyakov
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2011-11-17
Filing date: 2011-11-17
Publication date: 2014-08-28
Also published as: CN103917826A; EP2780636A1; CN103917826B; WO2013073984A1

Abstract

A turbomachine combustor assembly includes a combustor body having a combustor outlet, and a combustion liner arranged within the combustor body. The combustion liner defines a combustion chamber. An injection nozzle is arranged within the combustor body upstream from the combustion chamber. The injection nozzle is configured and disposed to deliver a first fluid toward the combustion chamber. A fluid module is mounted to the combustor body downstream from the combustion chamber. The fluid module includes a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.

Description

CROSS REFERENCE TO RELATED APPLICATION

This is a National Stage Application claiming priority to PCT Application No. PCT/RU2011/000908 filed Nov. 9, 2011, the entire contents of which are incorporated herein by reference.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a turbomachine combustor assembly.
In general, gas turbomachines combust a fuel/air mixture that releases heat energy to form a high temperature gas stream. The high temperature gas stream is channeled to a turbine portion via a hot gas path. The turbine portion converts thermal energy from the high temperature gas stream to mechanical energy that rotates a turbine shaft. The turbomachine may be used in a variety of applications, such as for providing power to a pump, an electrical generator, or aircraft.
Turbomachine efficiency increases as combustion gas stream temperatures increase. Unfortunately, higher gas stream temperatures produce higher levels of nitrogen oxide (NOx), an emission that is subject to both federal and state regulation. Therefore, there exists a careful balancing act between operating gas turbomachines in an efficient range, while also ensuring that the output of NOx remains below federal and state mandated levels. One method of achieving low NOx levels is to ensure good mixing of fuel and air prior to combustion and providing an environment that leads to more complete combustion of the fuel/air mixture.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect of the exemplary embodiment, a turbomachine combustor assembly includes a combustor body having a combustor outlet, and a combustion liner arranged within the combustor body. The combustion liner defines a combustion chamber. An injection nozzle is arranged within the combustor body upstream from the combustion chamber. The injection nozzle is configured and disposed to deliver a first fluid toward the combustion chamber. A fluid module is mounted to the combustor body downstream from the combustion chamber. The fluid module includes a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.
According to another aspect of the exemplary embodiment, a method of operating a turbomachine includes introducing a first fluid into a combustor assembly to establish a first fluid zone, introducing a second fluid into the combustor assembly to establish a second flame zone down stream of the first fluid zone, introducing a third fluid into the combustor assembly to establish a third fluid zone downstream of the second fluid zone, and combusting one or more of the first, second and third fluids to produce a hot gas stream to establish a first operating mode of the turbomachine.
According to yet another aspect of the exemplary embodiment, a turbomachine includes a compressor portion, a turbine portion operatively connected to the turbine portion, and a combustor assembly fluidly connected to the compressor portion and the turbine portion. The combustor assembly includes a combustor body, and a combustion liner arranged within the combustor body. The combustion liner defines a combustion chamber. An injection nozzle is arranged within the combustor body upstream from the combustion chamber. The injection nozzle is configured and disposed to introduce a first fluid toward the combustion chamber. A fluid module is mounted to the combustor body downstream from the combustion chamber. The fluid module includes a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWING

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 diagram of a turbomachine including a combustor assembly having a fluid module in accordance with the exemplary embodiment;

FIG. 2 is a partial perspective view of the combustor assembly of FIG. 1;

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

FIG. 4 is a schematic partial cross-sectional view of the fluid module in accordance with the exemplary embodiment;

FIG. 5 is a partial cross-sectional view of the combustor assembly of FIG. 2 illustrating a first operating mode in which fluid mixtures are introduced into first, second, and third fluid zones;

FIG. 6 is a partial cross-sectional view of the combustor assembly of FIG. 2 illustrating a second operating mode in which fluid mixtures are introduced into the first and second fluid zones; and

FIG. 7 is a partial cross-sectional view of the combustor assembly of FIG. 2 illustrating a third operating mode in which a fluid mixture is introduced into the first fluid zone.

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 FIG. 1, a turbomachine in accordance with an exemplary embodiment is indicated generally at 2. Turbomachine 2 includes a compressor portion 4 operatively connected to a turbine portion 6. Turbomachine 2 also includes a combustor assembly 8 that fluidly links compressor portion 4 and turbine portion 6. A common compressor/turbine shaft 10 mechanically links compressor portion 4 and turbine portion 6. With this arrangement, compressed air is passed into combustor assembly 8, mixed with fuel, and combusted to form hot gases. The hot gases are channeled to turbine portion 6 which converts thermal energy from the hot gases into mechanical rotational energy that is channeled to drive an external component such as a generator, a pump or other mechanically or fluidly driven mechanism.
As shown in FIGS. 2-3, combustor assembly 8 includes a combustor body 20 having an outer surface 22 and an inner surface 24. A combustor liner 30 is arranged within combustor body 20. Combustor liner 30 includes an outer surface portion 32 and an inner surface portion 34. Outer surface portion 32 is spaced from inner surface 24 of combustor body 20 to form a duct or passage 36. Combustor body 20 is also shown to include an upstream portion 37 and a downstream portion 39 between which define a combustion chamber 44. Combustor assembly 8 includes a plurality of injection nozzles, one of which is indicated at 50, supported by combustor body 20 and positioned at upstream portion 37 of combustor liner 30. Injection nozzle 50 injects a first fluid mixture 51 into combustion chamber 44. The first fluid mixture passes along a longitudinal axis of combustor assembly 8. The longitudinal axis should be understood to describe an axis of combustor assembly that extends between upstream portion 37 and downstream portion 39.
In accordance with the exemplary embodiment, combustor assembly 8 includes a fluid module 60 mounted at downstream portion 39 of combustor body 20. Fluid module 60 includes a fluid module body 62 that defines a fluid zone 64. Fluid module 60 also includes an inlet section 67 and an outlet section 69. Outlet section 69 joins with a transition piece 75. Transition piece 75 includes a duct 77 that delivers products of combustion to turbine portion 6. As will be discussed more fully below, duct 77 defines a combustion area 79.
In further accordance with the exemplary embodiment, fluid module 60 includes a plurality of first injector members 84 arranged in an annular array upstream relative to an annular array of a plurality of second injector members 86. The plurality of first injector members 84 receives fuel via a first fluid supply conduit 89 provided in combustor body 20. First fluid supply conduit 89 includes a first fluid inlet 90 that is configured to receive a first fluid. The first fluid could be a fuel, an inert gas or other liquid or gaseous mixture. Similarly, the plurality of second injector members receive a second fluid through a second fluid supply conduit 92 provided on combustor body 20. Second fluid supply conduit 92 includes a second fluid inlet 93 that is configured to receive a second fluid. In a manner similar to that described above, the second fluid could be fuel, an inert gas or other liquid or gaseous mixture. At this point it should be understood that the first and second fluids may be substantially identical or may be distinct one from the other depending upon desired operation parameters. In addition, each of the first and second injector members 84 and 86 include corresponding first and second third fluid inlets 96 and 97. Third fluid inlets may provide air from compressor portion 4 to each of the first and second injector members 84, 86 or some other liquid or gaseous mixture that is mixed with corresponding ones of the first and second fluids.
In still further accordance with the exemplary embodiment illustrated in FIG. 4, each first injector member 84 includes a first injector body 108 mounted to fluid module body 62 at a first orientation. First injector body 108 includes a third fluid passage 110 that is fluidly coupled to third fluid inlet 96 and a first fluid passage 112. First fluid passage 112 extends within third fluid passage 110 and is fluidly coupled to first fluid supply conduit 89. Each first injector member 84 is configured to introduce a second fluid mixture 119 into combustion zone 64. More specifically, each first injector member 84 is oriented to deliver a stream of the second fluid mixture that may include the first fluid and the third fluid along a radial axis into combustion zone 64. It should be understood that the term radial axis describes an axis that is substantially perpendicular to the longitudinal axis of the combustor assembly.
Each second injector member 86 includes a second injector body 130 mounted to fluid module body 62. Second injector body 130 includes a second third fluid passage 132 that is fluidly coupled to second third fluid inlet 97 and a second fluid passage 134. Second fluid passage 134 extends within second third fluid passage 132 and is fluidly coupled to second fluid supply conduit 92. Each second injector member 86 is configured to introduce a third fluid mixture 141 toward combustion area 79. More specifically, each second injector member 86 is oriented to deliver a mixture of the second and third fluids along an axis that is angled relative to the longitudinal axis and the radial axis. Each second injector member 86 is configured to deliver a third fluid mixture stream 142 downstream from second fluid mixture 119. Of course it should be understood that the particular angle can vary. Third fluid mixture may include both the second and third fluids.
With this arrangement, combustor assembly 8 can be operated in one of a plurality of modes depending upon a desired power output. In accordance with one aspect of the exemplary embodiment, combustor assembly 8 can be selectively operated in a first or base load mode in which first fluid mixture 51 defines a first combustible mixture and is combusted in a first fluid zone 154, second fluid mixture 119 defines a second combustible mixture and is combusted in a second fluid zone 157, and third fluid mixture 142 defines a third combustible mixture and is combusted in a third fluid zone 160 such as shown in FIG. 5. The three fluid zones 154, 157, and 159 lead to more complete combustion and establish a prolonged residence time of the fluid mixtures that leads to a more uniform heat release that results in lower combustion dynamics. It should be understood that the second mixture could include any air and/or inert gas to promote more complete combustion of the first and third mixtures.
Combustor assembly 8 can also be selectively operated in a second or first off-peak mode such as when desired power output is between about 40% and 70% of base load. In the second mode, the third fluid mixture does not contain any combustibles and may represent air or a mixture of inert gases. Alternatively, the third fluid mixture may simply be discontinued. In any case, in the second mode only the first and second fluid zones 154 and 157 are active such as shown in FIG. 6. Combustor assembly 8 may also be operated in a third mode such as when desired power output is between about 20% and 40% of base load. In the third mode, only first fluid zone 154 is active. The second and third fluid mixtures do not contain combustibles and may represent air or an inert gas mixture. Alternatively the second and third fluid mixtures may simply be discontinued.
At this point, it should be understood that the combustor assembly of the exemplary embodiment allows for the selective introduction of fluid mixtures into various positions along a combustion path. The fluid mixtures can all represent combustible mixtures or can represent mixtures of air or other inert fluids. Inert fluids can be introduced downstream from combustible fluids or may be introduced upstream of combustible fluids to facilitate more complete combustion. The introduction of inert fluids upstream of a combustion event has been shown to reduce undesirable emissions.
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

1. A turbomachine combustor assembly comprising:

a combustor body having a combustor outlet;

a combustion liner arranged within the combustor body, the combustion liner defining a combustion chamber;

an injection nozzle arranged within the combustor body upstream from the combustion chamber, the injection nozzle being configured and disposed to deliver a first fluid toward the combustion chamber; and

a fluid module mounted to the combustor body downstream from the combustion chamber, the fluid module including a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.

2. The turbomachine combustor assembly according to claim 1, wherein the injection nozzle is configured and disposed to deliver an axial stream of the first fluid toward the combustion chamber

3. The turbomachine combustor assembly according to claim 2, wherein the first injector member is configured to deliver a first radial stream of the second fluid into the fluid zone at the first orientation, and the second injector member is configured to deliver a second radial stream of the third fluid into the fluid zone at the second orientation.

4. The turbomachine combustor assembly according to claim 3, wherein the first orientation is substantially perpendicular to the fluid module body and the second orientation is angled downstream of the first orientation.

5. The turbomachine combustor assembly according to claim 1, wherein the first injector member includes a first plurality of injector members arranged in an annular array about the fluid module body and the second injector member includes a second plurality of injector members arranged in an annular array about the fluid module body.

6. The turbomachine combustor assembly according to claim 5, wherein the second plurality of injector members is arranged downstream relative to the first plurality of injector members.

7. The turbomachine combustor assembly according to claim 1, wherein the injection nozzle is configured and disposed to establish a first fluid zone, the first injector member is configured and disposed to establish a second fluid zone downstream from the first fluid zone, and the second injector member is configured to establish a third fluid zone downstream from the second fluid zone.

8. A method of operating a turbomachine comprising:

introducing a first fluid into a combustor assembly to establish a first fluid zone;

introducing a second fluid into the combustor assembly to establish a second fluid zone down stream of the first fluid zone;

introducing a third fluid into the combustor assembly to establish a third fluid zone downstream of the second fluid zone; and

combusting one or more of the first, second and third fluids to produce a hot gas stream to establish a first operating mode of the turbomachine.

9. The method of claim 8, wherein introducing the first fluid includes guiding a stream of the first fluid along a longitudinal axis of the combustor assembly.

10. The method of claim 9, wherein introducing the second fluid includes injecting a stream of the second fluid along a first radial axis of the combustor assembly.

11. The method of claim 10, wherein introducing the third fluid includes injecting a stream of the third fluid along a second radial axis of the combustor assembly, the second radial axis being angled relative to the first radial axis.

12. The method of claim 8, further comprising: ceasing introduction of the third fluid establishing a second operating mode of the turbomachine.

13. The method of claim 12, wherein establishing the second operating mode includes operating the turbomachine at about 40% to about 70% of the first operating mode.

14. The method of claim 12, further comprising: ceasing introduction of the second fluid establishing a third operating mode of the turbomachine.

15. The method of claim 14, wherein establishing the third operating mode includes operating the turbomachine at about 20% to about 40% of the first operating mode.

16. A turbomachine comprising:

a compressor portion;

a turbine portion operatively connected to the turbine portion; and

a combustor assembly fluidly connected to the compressor portion and the turbine portion, the combustor assembly comprising:

a combustor body;

an injection nozzle arranged within the combustor body upstream from the combustion chamber, the injection nozzle being configured and disposed to introduce a first fluid toward the combustion chamber; and

17. The turbomachine according to claim 16, wherein the injection nozzle is configured and disposed to deliver an axial stream of the first fluid toward the combustion chamber.

18. The turbomachine according to claim 16, wherein the first injector member is configured to deliver a radial stream of the second fluid into the fluid zone, and the second injector member is configured to deliver a radial stream of the third fluid into the fluid zone.

19. The turbomachine according to claim 16, wherein the injection nozzle is configured and disposed to establish a first fluid zone, the first injector member is configured and disposed to establish a second fluid zone down stream from the first fluid zone, and the second injector member is configured to establish a third fluid zone downstream from the second fluid zone.

20. The turbomachine according to claim 18, further comprising: a transition piece fluidly connecting the combustor assembly and the turbine portion, at least a portion of one the third fluid zone residing in the transition piece.