Patent Application
20180245792
The present invention generally involves a combustion system of a gas turbine. More specifically, the invention relates to a combustion system including axially staged fuel injection.
A typical turbomachine includes a compressor to compress inlet air, a combustor in which the compressed inlet air is combusted along with fuel, a turbine in which products of the combustion are receivable for power generation purposes and a transition piece. The transition piece is fluidly interposed between the combustor and the turbine.
In some cases, the typical turbomachine is configured to support axially staged or late lean injection. In these cases, a secondary fuel-air mixture is injected into downstream sections of the combustor or the transition piece in order to cause secondary combustion within the downstream sections of the combustor or the transition piece. This secondary combustion tends to reduce emissions of pollutants, such as oxides of nitrogen.
Aspects and advantages are set forth below in the following description, or may be obvious from the description, or may be learned through practice.
One embodiment of the present disclosure is an axially staged combustion system. The axially staged combustion system includes a primary fuel nozzle, a primary combustion zone defined downstream from the primary fuel nozzle, a conical duct disposed downstream from the primary combustion zone and an integrated exit piece disposed downstream from the conical duct. The conical duct and the integrated exit piece at least partially form a hot gas path of the duct section. A plurality of fuel injectors is oriented radially inwardly with respect to an axial centerline of the duct section and is disposed downstream from the primary combustion zone. Each fuel injector of the plurality of fuel injectors provides for injection of a secondary fuel-air mixture into the hot gas path. The plurality of fuel injectors is distributed along at least one of the conical duct and the integrated exit piece.
Another embodiment of the present disclosure is a combustion section. The combustion section includes a plurality of duct sections annularly arranged about a common axial centerline. Each duct section comprises a primary combustion zone that is defined downstream from a primary fuel nozzle, a conical duct that extends downstream from the primary combustion zone and an integrated exit piece that is disposed downstream from the conical duct. The conical duct and the integrated exit piece at least partially form a hot gas path of the duct section. A plurality of fuel injectors is oriented radially inwardly with respect to an axial centerline of the duct section and is disposed downstream from the primary combustion zone. Each fuel injector of the plurality of fuel injectors provides for injection of a secondary fuel-air mixture into the hot gas path. The plurality of fuel injectors is distributed along at least one of the conical duct and the integrated exit piece.
Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.
A full and enabling disclosure of various embodiments, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:
Reference will now be made in detail to present embodiments of the disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the disclosure.
As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. The term “radially” refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term “axially” refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component, and the term “circumferentially” refers to the relative direction that extends around the axial centerline of a particular component.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
Each example is provided by way of explanation, not limitation. In fact, it will be apparent to those skilled in the art that modifications and variations can be made without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents. Although exemplary embodiments of the present disclosure will be described generally in the context of a combustor for a land based power generating gas turbine for purposes of illustration, one of ordinary skill in the art will readily appreciate that embodiments of the present disclosure may be applied to any style or type of combustor for a turbomachine and are not limited to combustors or combustion systems for land based power generating gas turbines unless specifically recited in the claims.
Referring now to the drawings,
During operation, air 20 flows into the compressor 12 where the air 20 is progressively compressed, thus providing compressed or pressurized air 22 to the combustion section 14. At least a portion of the compressed air 22 is mixed with a fuel 24 within each can combustor of the combustion section 14 and burned to produce combustion gases 26. The combustion gases 26 flow from the combustor 14 into the turbine 16, wherein energy (kinetic and/or thermal) is transferred from the combustion gases 26 to rotor blades (not shown), thus causing shaft 18 to rotate. The mechanical rotational energy may then be used for various purposes such as to power the compressor 12 and/or to generate electricity. The combustion gases 26 may then be exhausted from the gas turbine 10.
In particular embodiments, each duct section 30 includes, in serial flow order, a cylindrical liner or duct 100, a conical liner or duct 200 coupled to and positioned immediately downstream from and/or adjacent to the cylindrical duct 100, and an integrated exit piece 300 disposed downstream from the conical duct 200. In particular embodiments, the cylindrical duct 100 is disposed downstream and/or extends downstream from one or more primary or axially oriented fuel nozzles 40.
In particular embodiments, the cylindrical duct 100 may at least partially define a primary combustion or reaction zone 42 that is downstream from the primary fuel nozzle(s) 40. The cylindrical duct 100, the conical duct 200 and the integrated exit piece 300 together at least partially form the hot gas path 38 of the respective duct section 30. Each respective integrated exit piece 300 is interconnected with two circumferentially adjacent integrated exit pieces 300 such that the collective of integrated exit pieces 300 forms the annular chamber 36 (
In particular embodiments, as shown in
In particular embodiments, as illustrated in
A forward end 402 of the intermediate duct 400 may be connected to or joined with the aft end 208 of the conical duct 200 at joint 50. An aft end 404 of the intermediate duct 400 may be connected to or joined with the inlet end 302 of the integrated exit piece 300 at joint 52. As shown in
In various embodiments, as shown in
In various embodiments, the plurality of fuel injectors 500 may be distributed along any one of the cylindrical duct 100, the conical duct 200, the intermediate duct 400, the exit piece 300 or any combination thereof. For example, in one embodiment, the plurality of fuel injectors 500 is distributed across the cylindrical duct 100. In one embodiment, the plurality of fuel injectors 500 is distributed across the conical duct 200. In one embodiment, at least one fuel injector 500 of the plurality of fuel injectors 500 is distributed across the inlet exit piece 300. In one embodiment, as shown in
In one embodiment, as illustrated in
In one embodiment, at least one fuel injector 502 of the plurality of fuel injectors 500 is positioned along the inlet chamber 304. In one embodiment, at least one fuel injector 500 of the plurality of fuel injectors 500 is positioned along the radially extending side wall 310 of the connection segment 308. In one embodiment, at least one fuel injector 502 of the plurality of fuel injectors 500 is positioned along the aft extending inner wall 312 of the connection segment 308. In one embodiment, at least one fuel injector 502 of the plurality of fuel injectors 500 is positioned along the aft extending outer wall 314 of the connection segment 308. In one embodiment, at least one fuel injector 502 of the plurality of fuel injectors 500 is positioned along the connection flange 316 of the connection segment 308.
In particular embodiments, as illustrated in
In particular embodiments, as illustrated in
In particular embodiments, as illustrated in
Advantageously, the fuel injectors 500, 502, 504, 506, 508 provides the ability to reduce undesirable emissions generated during the combustion process, while providing flexibility to the overall combustion section 14. Axially staged or late lean injection can also allow for an injection of multiple gas streams, including alternate gases, such as refinery gases, into the hot gas path 38 that non-axially staged combustions systems are generally unable to handle.
This written description uses examples to disclose the invention, including the best mode, and to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.
