FULLY PREMIXED SECONDARY FUEL NOZZLE WITH IMPROVED STABILITY

Abstract

A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Description

BACKGROUND OF THE INVENTION

[0001] 1. Field of the Invention

[0002] This invention relates generally to a fuel and air injection apparatus and method of operation for use in a gas turbine combustor for power generation and more specifically to a device that reduces the emissions of nitrogen oxide (NOx) and other pollutants by injecting fuel into a combustor in a premix condition.

[0003] 2. Description of Related Art

[0004] In an effort to reduce the amount of pollution emissions from gas-powered turbines, governmental agencies have enacted numerous regulations requiring reductions in the amount of emissions, especially nitrogen oxide (NOx) and carbon monoxide (CO). Lower combustion emissions can be attributed to a more efficient combustion process, with specific regard to fuel injectors and nozzles. Early combustion systems utilized diffusion type nozzles that produce a diffusion flame, which is a nozzle that injects fuel and air separately and mixing occurs by diffusion in the flame zone. Diffusion type nozzles produce high emissions due to the fact that the fuel and air burn stoichiometrically at high temperature. An improvement over diffusion nozzles is the utilization of some form of premixing such that the fuel and air mix prior to combustion to form a homogeneous mixture that burns at a lower temperature than a diffusion type flame and produces lower NOx emissions. Premixing can occur either internal to the fuel nozzle or external thereto, as long as it is upstream of the combustion zone. Some examples of prior art found in combustion systems that utilize some form of premixing are shown in FIGS. 1 and 2.

[0005] Referring to FIG. 1, a fuel nozzle 10 of the prior art for injecting fuel and air is shown. This fuel nozzle includes a diffusion pilot tube 11 and a plurality of discrete pegs 12, which are fed fuel from conduit 13. Diffusion pilot tube 11 injects fuel at the nozzle tip directly into the combustion chamber through swirler 14 to form a stable pilot flame. Though this pilot flame is stable, it is extremely fuel rich and upon combustion with compressed air, this pilot flame is high in nitrogen oxide (NOx) emissions.

[0006] Another example of prior art fuel nozzle technology is the fuel nozzle 20 shown in FIG. 2, which includes a separate, annular manifold ring 21 and a diffusion pilot tube 22. Fuel flows to the annular manifold ring 21 and diffusion pilot tube 22 from conduit 23. Diffusion pilot tube 22 injects fuel at the nozzle tip directly into the combustion chamber through swirler 24. Annular manifold ring 21 provides an improvement over the fuel nozzle of FIG. 1 by providing an improved fuel injection pattern and mixing via the annular manifold instead of through radial pegs. The fuel nozzle shown in FIG. 2 is described further in U.S. Pat. No. 6,282,904, assigned to the same assignee as the present invention. Though this fuel nozzle attempts to reduce pollutant emissions over the prior art, by providing an annular manifold to improve fuel and air mixing, further improvements are necessary regarding a significant source of emissions, the diffusion pilot tube 22. The present invention seeks to overcome the shortfalls of the fuel nozzles described above by providing a fuel nozzle that is completely premixed, thus eliminating all sources of a diffusion flame, while still being capable of providing a stable pilot flame for a constant combustion process.

SUMMARY OF THE INVENTION

[0007] It is an object of the present invention to provide a premixed fuel nozzle for a gas turbine engine that reduces NOx and other air pollutants during operation.

[0008] It is another object of the present invention to provide a premixed fuel nozzle with an injector assembly comprising a plurality of radially extending fins to inject fuel and air into the combustor such that the fuel and air premixes, resulting in a more uniform injection profile for improved combustor performance.

[0009] It is yet another object of the present invention to provide, through fuel hole placement, an enriched fuel air shear layer to enhance combustor lean blowout margin in the downstream flame zone.

[0010] It is yet another object of the present invention to provide a premixed fuel nozzle with improved combustion stability through the use of a plurality of fuel injection orifices located along a conical surface of the premixed fuel nozzle.

[0011] In accordance with these and other objects, which will become apparent hereinafter, the instant invention will now be described with particular reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

[0012] FIG. 1 is a cross section view of a fuel injection nozzle of the prior art.

[0013] FIG. 2 is a cross section view of a fuel injection nozzle of the prior art.

[0014] FIG. 3 is a perspective view of the present invention.

[0015] FIG. 4 is a cross section view of the present invention.

[0016] FIG. 5 is a detail view in cross section of the injector assembly of the present invention.

[0017] FIG. 6 is an end elevation view of the nozzle tip of the present invention.

[0018] FIG. 7 is a cross section view of the present invention installed in a combustion chamber.

[0019] FIG. 8 is a perspective view of an alternate embodiment of the present invention.

[0020] FIG. 9 is a detail view in cross section of an alternate embodiment of the injector assembly of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

[0021] A premix fuel nozzle 40 is shown in detail in FIGS. 3 through 6. Premix fuel nozzle 40 has a base 41 with three through holes 42 for bolting premix fuel nozzle 40 to a housing 75 (see FIG. 7). Extending from base 41 is a first tube 43 having a first outer diameter, a first inner diameter, a first thickness, and opposing first tube ends. Within premix fuel nozzle 40 is a second tube 44 having a second outer diameter, a second inner diameter, a second thickness, and opposing second tube ends. The second outer diameter of second tube 44 is smaller than the first inner diameter of first tube 43 thereby forming a first annular passage 45 between the first and second tubes, 43 and 44, respectively. Premix fuel nozzle 40 further contains a third tube 46 having a third outer diameter, a third inner diameter, a third thickness, and opposing third tube ends. The third outer diameter of third tube 46 is smaller than said second inner diameter of second tube 44, thereby forming a second annular passage 47 between the second and third tubes 44 and 46, respectively. Third tube 46 contains a third passage 48 contained within the third inner diameter.

[0022] Premix nozzle 40 further comprises an injector assembly 49, which is fixed to each of the first, second, and third tubes, 43, 44, and 46, respectively, at the tube ends thereof opposite base 41. Injector assembly 49 includes a plurality of radially extending fins 50, each of the fins having an outer surface, an axial length, a radial height, and a circumferential width. Each of fins 50 are angularly spaced apart by an angle α of at least 30 degrees and fins 50 further include a first radially extending slot 51 within fin 50 and a second radially extending slot 52 within fin 50, a set of first injector holes 53 located in the outer surface of each of fins 50 and in fluid communication with first slot 51 therein. A set of second injector holes, 54 and 54A are located in the outer surface of each of fins 50 and in fluid communication with second slot 52 therein. Fixed to the radially outermost portion of the outer surface of fins 50 to enclose slots 51 and 52 are fin caps 55. Injector assembly 49 is fixed to premix nozzle 40 such that first slot 51 is in fluid communication with first passage 45 and second slot 52 is in fluid communication with second passage 47. Premix nozzle 40 further includes a fourth tube 80 having a generally conical shape with a tapered outer surface 81, a fourth inner diameter, and opposing fourth tube ends. Fourth tube 80 is fixed at fourth tube ends to injector assembly 49, opposite first tube 43 and second tube 44, and to third tube 46. The fourth inner diameter of fourth tube 80 is greater in diameter than the third outer diameter of third tube 46, thereby forming a fourth annular passage 82, which is in fluid communication with second passage 47. Premix fuel nozzle 40 further includes a cap assembly 56 fixed to the forward end of fourth tube 80 and includes an effusion plate 57 having an end surface including a set of third injector holes 58 therein. The use of a conical shaped tube as fourth tube 80 allows a smooth transition in flow path between injector assembly 49 and cap assembly 56 such that large zones of undesirable recirculation, downstream of fins 50, are minimized. If the recirculation zones are not minimized, they can provide an opportunity for fuel and air to mix to the extent that combustion occurs and is sustainable upstream of the desired combustion zone.

[0023] The premix fuel nozzle 40, in the present embodiment, injects fluids, such as natural gas and compressed air into a combustor of a gas turbine engine for the purposes of establishing a premixed pilot flame and supporting combustion downstream of the fuel nozzle. One operating embodiment for this type of fuel nozzle is in a dual stage, dual mode combustor similar to that shown in FIG. 7. A dual stage, dual mode combustor 70 includes a primary combustion chamber 71 and a secondary combustion chamber 72, which is downstream of primary chamber 71 and separated by a venturi 73 of reduced diameter. Combustor 70 further includes an annular array of diffusion type nozzles 74 each containing a first annular swirler 76. Premix fuel nozzle 40 of the present invention is located along center axis A-A of combustor 70, upstream of second annular swirler 77, and is utilized as a secondary fuel nozzle to provide a pilot flame to secondary combustion chamber 72 and to further support combustion in the secondary chamber. In operation, flame is first established in primary combustion chamber 71, which is upstream of secondary combustion chamber 72, by an array of diffusion-type fuel nozzles 74, then a pilot flame is established in secondary combustion chamber 72. Fuel flow is then increased to secondary fuel nozzle 40 to establish a more stable flame in secondary combustion chamber 72, while flame is extinguished in primary combustion chamber 71, by cutting off fuel flow to diffusion-type nozzles 74. Once a stable flame is established in secondary combustion chamber 72 and flame is extinguished in primary combustion chamber 71, fuel flow is restored to diffusion-type nozzles 74 and fuel flow is reduced to secondary fuel nozzle 40 such that primary combustion chamber 71 now serves as a premix chamber for fuel and air prior to entering secondary combustion chamber 72. The present invention will now be described in detail with reference to the particular operating environment described above.

[0024] In the preferred embodiment, the premix nozzle 40 operates in a dual stage dual mode combustor 70, where premix nozzle 40 serves as a secondary fuel nozzle. The purpose of the nozzle is to provide a source of flame for secondary combustion chamber 72 and to assist in transferring the flame from primary combustion chamber 71 to secondary combustion chamber 72. In this role, the second passage 47, second slot 52, and second set of injector holes 54 and 54A flow a fuel, such as natural gas into plenum 78 where it is mixed with compressed air prior to combusting in secondary combustion chamber 72. During engine start-up, first passage 45, first slot 51, and first set of injector holes 53 flow compressed air into the combustor to mix with the fuel. In an effort to maintain machine load condition when the flame from primary combustion chamber 71 is transferred to secondary combustion chamber 72, first passage 45, first slot 51, and first set of injector holes 53 flow fuel, such as natural gas, instead of air, to provide increased fuel flow to the established flame of secondary combustion chamber 72. Once the flame is extinguished in primary combustion chamber 71 and securely established in secondary combustion chamber 72, fuel flow through the first passage 45, first slot 51, and first set of injector holes 53 of premix nozzle 40 is slowly cut-off and replaced by compressed air, as during engine start-up. During this entire process, compressed air is flowing through third passage 48 and third set of injector holes 58 to provide adequate cooling to the nozzle cap assembly 56.

[0025] NOx emissions are reduced through the use of this premix nozzle by ensuring that all fuel that is injected is thoroughly mixed with compressed air prior to reaching the flame front of the combustion zone. This is accomplished by the use of the fin assembly 49 and through proper sizing and positioning of injector holes 53, 54, and 54A. Thorough analysis has been completed regarding the sizing and positioning of the first and second set of injector holes, such that the injector holes provide a uniform fuel distribution. To accomplish this task, first set of injector holes 53, having a diameter of at least 0.050 inches, are located in a radially extending pattern along the outer surfaces of fins 50 as shown in FIG. 3. To facilitate manufacturing, first set of injector holes 53 have an injection angle relative to the fin outer surface such that fluids are injected upstream towards base 41. Second set of injector holes, including holes 54 on the forward face of fins 50 and 54A on outer surfaces of fin 50, proximate fin cap 55, are each at least 0.050 inches in diameter. Injector holes 54A are generally perpendicular to injector holes 54, and have a slightly larger flow area than injector holes 54. Second set of injector holes 54 and 54A are placed at strategic radial locations on fins 50 so as to obtain an ideal degree of mixing which both reduces emissions and provides a stable shear layer flame in secondary combustion chamber 72. To further provide a uniform fuel injection pattern and to enhance the fuel and air mixing characteristics of the premix nozzle, all fuel injectors are located upstream of second annular swirler 77.

[0026] In the preferred embodiment, compressed air flows through third set of injector holes 58 for cooling the cap assembly 56. Cooling efficiency is enhanced when using effusion cooling due to the amount of material that is cooled for a given amount of air. That is, an angled cooling hole has a greater surface area of hot material that is cooled using the same amount of cooling air as other cooling methods. In order to provide an effective cooling scheme for the cap assembly, the third set of injector holes 58, which are located in effusion plate 57, have an injection axis that intersects the end surface of effusion plate 57 at an angle β up to 20 degrees relative to an axis perpendicular to the end surface of effusion plate 57, and have a diameter of at least 0.020 inches.

[0027] An alternate embodiment of the present invention is shown in FIGS. 8 and 9. The alternate embodiment includes all of the elements of the preferred embodiment as well as a fourth set of injector holes 83, which are in communication with fourth annular passage 82 of fourth tube 80. These injector holes provide an additional source of fuel for combustion. The additional fuel from fourth set of injector holes 83 premixes with fuel and air, from injector assembly 49, in passage 78 (see FIG. 7) to provide a more stable flame, through a more fuel rich premixture, in the shear layer of the downstream flame zone region 90. Fourth set of injector holes 83 are placed about the conical surface 81 of fourth tube 80, between injector assembly 49 and cap assembly 56, and have a diameter of at least 0.025 inches.

[0028] While the invention has been described in what is known as presently the preferred embodiment, it is to be understood that one skilled in the art of combustion and gas turbine technology would recognize that the invention is not to be limited to the disclosed embodiment but, on the contrary, is intended to cover various modifications and equivalent arrangements within the scope of the following claims.

Claims

1. A premix fuel nozzle for use in a gas turbine comprising: a base; a first tube having a first outer diameter, a first inner diameter, a first thickness, and opposing first tube ends, said base fixed to said first tube at one of said first tube ends; a second tube coaxial with said first tube and having a second outer diameter, a second inner diameter, a second thickness, and opposing second tube ends, one of said second tube ends adjacent said base, said second outer diameter smaller than said first inner diameter thereby forming a first annular passage between said first and second tubes; a third tube coaxial with said second tube and having a third outer diameter, a third inner diameter, a third thickness, and opposing third tube ends, one of said third tube ends adjacent said base, said third outer diameter smaller than said second inner diameter thereby forming a second annular passage between said second and third tubes, said third tube having a third passage contained within said third inner diameter; an injector assembly fixed to each of said first and second tubes at said tube ends thereof opposite said base, said injector assembly having a plurality of radially extending fins, each of said fins having an outer surface, an axial length, a radial height, and a circumferential width, a first radially extending slot within said fin and a second radially extending slot within said fin, a set of first injector holes located in the outer surface of each of said fins and in fluid communication with said first slot therein, a set of second injector holes located in the outer surface of each of said fins and in fluid communication with said second slot therein, and a fin cap fixed to the radially outermost portion of the outer surface of said fin to enclose said slots; a fourth tube coaxial with said third tube and of generally conical shape with a tapered outer surface and a fourth inner diameter, said fourth tube having opposing fourth tube ends, one of said fourth tube ends fixed to said injector assembly opposite said first and second tubes said other fourth tube end fixed to said third tube, said fourth inner diameter greater than said third outer diameter thereby forming a fourth annular passage, said fourth annular passage in fluid communication with said second passage; a cap assembly fixed to said fourth tube and having a fifth outer diameter and a fifth inner diameter, said cap assembly further comprising an effusion plate having a third set of injector holes; and, wherein each of said first slots is in fluid communication with said first passage and each of said second slots is in fluid communication with said second passage.

2. The premix fuel nozzle of claim 1 wherein said first passage and each of said first slots and first injector holes flow natural gas or compressor air into a combustor, depending on combustor mode, of operation.

3. The premix fuel nozzle of claim 1 wherein said second passage, and each of said second slots and second injector holes flow natural gas into a combustor.

4. The premix fuel nozzle of claim 1 where in said third passage and third injector holes injects compressor discharge air into the combustor.

5. The premix fuel nozzle of claim 1 where in said fourth tube includes a fourth set of injector holes in fluid communication with said fourth annular passage and arranged around said tapered outer surface of said fourth tube.

6. The premix fuel nozzle of claim 5 where in said fourth passage and fourth set of injector holes flow natural gas into a combustor.

7. The premix nozzle according to claim 5 wherein said fourth set of injector holes in said fourth tube are at least 0.025 inches in diameter.

8. The premix fuel nozzle of claim 1 wherein each of said injector holes of said first set in each of said fins are at least 0.050 inches in diameter.

9. The premix nozzle of claim 1 wherein said each of first injector holes is angled so as to discharge towards said nozzle base.

10. The premix fuel nozzle of claim 1 wherein each of said second injector holes has a flow area and for each of said fins said flow area of at least one of said second injector holes immediately adjacent said fin cap is greater than the flow area of each of the remaining said second set of injector holes nearest said first tube.

11. The premix fuel nozzle of claim 10 wherein each of said second injector holes is at least 0.050 inches in diameter.

12. The premix fuel nozzle of claim 10 wherein said second set of injector holes is angled in a direction away from said base.

13. The premix fuel nozzle of claim 1 wherein said fins are spaced apart circumferentially by an angle α of at least 30 degrees.

14. The premix fuel nozzle of claim 1 wherein said effusion plate has an outer surface, each of said third injector holes has an injection axis, and each of said injection axes intersects said outer surface of said effusion plate at an angle β of not more than 20 degrees relative to an axis perpendicular to said effusion plate.

15. The premix fuel nozzle of claim 14 wherein each of said third injector holes in said effusion plate is at least 0.020 inches in diameter.

16. An improved gas turbine combustor comprising: a combustion liner with primary and secondary combustion chambers interconnected by a venturi, said venturi having a throat region being of reduced dimension compared to said primary and secondary combustion chambers; a plurality of diffusion type fuel nozzles in an annular array upstream from said primary combustion chamber for introducing fuel into said primary combustion chamber, each of said diffusion nozzles including a first annular swirler for introducing pressurized air into said primary combustion chamber for creating a combustible fuel air mixture; a second annular swirler located in said combustion liner upstream of said secondary combustion chamber; a fully premixed secondary fuel nozzle having an outer surface with a portion of said outer surface being conically tapered and containing a plurality of fuel injectors, said fully premixed nozzle positioned upstream from said secondary combustion chamber and having a discharge end directed into said secondary combustion chamber; and where in all of said fuel injectors are located upstream of said second annular swirler.

17. A method of operating a gas turbine combustor to reduce pollutant emissions comprising: providing a combustion liner with primary and secondary combustion chambers interconnected by a venturi, said venturi having a throat region being of reduced dimension compared to said primary and secondary combustion chambers; providing a plurality of diffusion type fuel nozzles in an annular array upstream from said primary combustion chamber for introducing fuel into said primary combustion chamber, each of said diffusion nozzles including a first annular swirler for introducing pressurized air into said primary combustion chamber for creating a combustible fuel air mixture; providing a second annular swirler upstream of said secondary combustion chamber; providing a fully premixed secondary fuel nozzle having an outer surface with a portion of said outer surface being conically tapered and containing a plurality of fuel injectors, said fully premixed nozzle positioned upstream from said secondary combustion chamber and having a discharge end directed into said secondary combustion chamber; and, discharging all fuel from said secondary fuel nozzle upstream of said second annular swirler.