Gas turbine combustor

Abstract

The invention relates to a gas turbine combustor (10) comprising a combustion chamber (11) with a flame tube (12), wherein the flame tube (12) defines a combustion zone (13) of the gas turbine combustor for combusting fuel in the presence of combustion air, a main burner (14), a pilot burner (15), wherein the main burner (14) surrounds the pilot burner (15) radially outward, wherein the main burner (14) is designed as a jet burner with jet pipes (16) extending in a straight line and is configured to introduce a mixture of fuel and combustion air in a straight flow into a radially outer portion of the combustion zone (13), wherein the pilot burner (15) is designed as a swirl burner with a defined number of swirl pipes (17) extending in a helical shape or solenoid shape or as a cone burner or a converging burner and is configured to introduce a mixture of fuel and combustion air in a swirl flow into a radially inner portion of the combustion zone (13), wherein a ratio FH / FP between a surface (FH) of the main burner (14) through which combustion air flows and an area (FP) of the pilot burner (15) through which combustion air flows is between 3 and 6.

Description

Technical Field

[0001] This invention relates to gas turbine combustors. Background Technology

[0002] DE 102018125848 A1 discloses a gas turbine combustor configured for burning a mixture of combustion air and gaseous fuel in a gaseous fuel operating mode and for burning liquid fuel in the presence of combustion air in a liquid fuel operating mode. The gas turbine combustor disclosed therein has a combustion chamber including a flame tube and a pre-combustion chamber upstream of the flame tube. In the gaseous fuel operating mode, the mixture of gaseous fuel and combustion air is fed into the combustion chamber via a main swirling fluid. In the liquid fuel operating mode, the liquid fuel is fed into the combustion chamber via an atomizing device, and the combustion air is fed into the combustion chamber via the main swirling fluid.

[0003] DE 102020116245 A1 discloses another gas turbine combustor with a combustion chamber comprising a flame tube and a pre-combustion chamber. Combustion air is externally guided through the flame tube and fed into the combustion chamber via a swirling fluid. Mixing of the combustion air with the gaseous fuel then occurs in the region of the swirling fluid. A portion of the combustion air may pass directly into the flame tube via the swirling fluid.

[0004] DE 102021123513 A1 includes a gas turbine combustor implemented as a swirl combustor. The swirl combustor has multiple swirl tubes spirally or helically coiled around a central axis, wherein gaseous fuel and combustion air can be mixed in the inlet region of the swirl tubes. The outlet region of the swirl tubes leads to the combustion chamber.

[0005] DE 19737997 A1 and DE 19510743 A1 disclose a gas turbine burner designed as a conical burner or a tapered burner. In the region of the conical burner (which is also called a tapered burner), the gas can be mixed with combustion air to provide a mixture of gas and combustion air to the actual combustion chamber. Summary of the Invention

[0006] There is a need for a gas turbine combustor by means of which natural gas and hydrogen, as gaseous fuels, can be burned stably with low emissions. This has been possible only to a limited extent with respect to known concepts of gas turbine combustors. Therefore, the object of the present invention is to provide a gas turbine combustor by means of which both natural gas and hydrogen can be burned stably and with low emissions. This object is achieved by the gas turbine combustor according to claim 1.

[0007] The gas turbine burner according to the invention includes a combustion chamber having a flame tube, wherein the flame tube defines a combustion zone of the gas turbine burner for burning fuel in the presence of combustion air.

[0008] The gas turbine burner according to the present invention includes a main burner and a pilot burner, wherein the main burner surrounds the pilot burner radially outward.

[0009] The main burner of the gas turbine burner according to the invention is designed as a jet burner having preferably 40 to 120 jet tubes extending in a straight line, and the main burner is configured to introduce a mixture of fuel and combustion air into the radially outer portion of the combustion zone in a straight flow.

[0010] The ignition burner of the gas turbine burner according to the invention is designed as a swirl burner having a limited number of spirally or helically extending swirl tubes, or as a conical burner or a tapered burner, and is configured to introduce a mixture of fuel and combustion air into the radially inner portion of the combustion zone by a swirling flow.

[0011] In the gas turbine burner according to the invention, the ratio FH / FP between the area FH of the main burner through which the combustion air flows and the area FP of the ignition burner through which the combustion air flows is between 3 and 6.

[0012] The area FH of the main burner through which combustion air flows is obtained from the sum of the minimum cross-sectional areas of all the jet tubes of the main burner along their length or axial extent. Assuming all jet tubes are implemented identically, the area FH of the main burner through which combustion air flows is obtained by multiplying the minimum cross-sectional area of ​​one of the jet tubes by the number of jet tubes.

[0013] Then, when the ignition burner is implemented as a swirl burner, the area FP of the ignition burner through which the combustion air flows is obtained from the sum of the minimum cross-sectional areas of all the swirl tubes along their length or axial extent. Assuming that all the swirl tubes are implemented identically, the area FP of the ignition burner designed as a swirl burner through which the combustion air flows is obtained by multiplying the minimum cross-sectional area of ​​one of the swirl tubes by the number of swirl tubes.

[0014] Then, when the ignition burner is implemented as a conical burner or a tapered burner, the area FP of the ignition burner through which the combustion air flows is obtained from the minimum cross-sectional area of ​​the hollow space of the conical burner or tapered burner, which radially inner limits the body of the conical burner or tapered burner, which forms a section of the cone of the conical burner or tapered burner.

[0015] The gas turbine combustor according to the invention includes a main combustor and an ignition combustor. The main combustor is implemented as a jet combustor and surrounds the ignition combustor radially outward. The ignition combustor is a swirl combustor with a swirl tube, a conical combustor, or a tapered combustor. Both hydrogen and natural gas can be burned in a stable manner with low emissions.

[0016] Preferably, the main combustor is equipped to mix fuel and combustion air in the inlet region of the jet tube extending in a straight line, wherein the ratio l / d between the mixing section l of the jet tube and the diameter d of the jet tube is greater than 5, preferably greater than 10. This diameter d of the jet tube is the minimum diameter of the jet tube along its length or axial direction.

[0017] Specifically, when the ignition burner is designed as a swirl burner, it is equipped to mix fuel and combustion air in the inlet region of the swirl tube, wherein the ratio l / d between the mixing section l of the swirl tube and the diameter d of the swirl tube is greater than 5, preferably greater than 10. This diameter d of the swirl tube is the minimum diameter of the swirl tube along its length or axial direction.

[0018] Specifically, when the ignition burner is designed as a conical or tapered burner, it is equipped to mix a first portion of the gas with combustion air immediately upstream of the flame tube, and a second, smaller portion of the gas with combustion air further upstream of the flame tube. This is preferred in order to burn both natural gas and hydrogen in a stable manner with low emissions.

[0019] Preferably, the ratio FH / FP between the area FH of the main burner through which the combustion air flows and the area FP of the ignition burner through which the combustion air flows is between 3 and 5, preferably between 3.5 and 4.5; or between 4 and 6, preferably between 4.5 and 5.5. These ratios between the area of ​​the main burner through which the combustion air flows and the area of ​​the ignition burner through which the combustion air flows are particularly suitable for burning both natural gas and hydrogen in a stable manner with low emissions.

[0020] Preferably, the main burner includes jet tubes extending in a straight line, with between 40 and 100, more preferably between 60 and 80. This is also preferred in order to burn both natural gas and hydrogen in a stable manner with low emissions.

[0021] Preferably, a resonator chamber is formed between the main burner and the ignition burner, the resonator chamber opening into the combustion zone of the gas turbine burner defined by the flame tube. This avoids self-excited acoustic instability during operation. The resonator chamber formed between the main burner and the ignition burner acoustically stabilizes the gas turbine burner and reduces the risk of damage to it.

[0022] Preferably, the gas turbine combustor includes a fuel passage equipped for feeding fuel to the main combustor and the ignition combustor, wherein the fuel passage is formed in a plate shape on the portion facing the main combustor and the ignition combustor, and in a roof-like or arched shape on the portion facing away from the main combustor and the ignition combustor. In this way, it is possible to reduce thermal stress in the fuel passage and thus reduce the risk of damage to the fuel passage due to material embrittlement and / or plastic deformation.

[0023] Features related to the fuel passage and features related to the resonator chamber can also be advantageously employed, while features related to the ratios FH / FP and l / d on the gas turbine combustor are irrelevant. Attached Figure Description

[0024] Preferred further developments of the invention are obtained from the dependent claims and the following description. Exemplary embodiments of the invention are explained in more detail with the aid of the accompanying drawings, but are not limited thereto. In the drawings: Figure 1 A partial cross-sectional view of a first gas turbine combustor according to the invention is shown. Figure 2 A partial cross-sectional view of a second gas turbine combustor according to the present invention is shown. Detailed Implementation

[0025] Figure 1 A partial cross-sectional view of a first gas turbine combustor 10 according to the present invention is shown. The gas turbine combustor 10 includes a combustion chamber 11, which includes a flame tube 12. The flame tube 12 defines a combustion zone 13 of the gas turbine combustor 10, in which fuel is burned in the presence of combustion air.

[0026] The gas turbine combustor 10 has a main combustor 14 and an ignition combustor 15, wherein the main combustor 14 surrounds the ignition combustor 15 radially outward. A mixture of fuel and combustion air is introduced into the radially outer portion of the combustion zone 13 defined by the flame tube 12 via the main combustor 14. A mixture of fuel and combustion air is introduced into the radially inner portion of the combustion zone 13 via the ignition combustor 15.

[0027] Figure 1 The main burner 14 shown is designed as a jet burner with jet tubes 16 extending in a straight line, wherein the main burner 14, or the jet tubes 16 extending in a straight line, is designed and constructed to introduce a mixture of fuel and combustion air into the radially outer portion of the combustion zone 13 defined by the flame tubes 12 in a straight flow. All jet tubes 16 of the main burner 14 can be implemented in the same manner and are therefore implemented identically.

[0028] exist Figure 1 In an exemplary embodiment, the ignition burner 15, radially positioned within the main burner 14, is designed as a swirl burner with helically or spirally extending swirl tubes 17, wherein the swirl burner is configured to introduce a mixture of fuel and combustion air into the radially inner portion of the combustion zone 13 in a swirling flow. All swirl tubes 17 of the ignition burner 15 may be implemented identically and therefore in the same manner.

[0029] Figure 1 A fuel nozzle 18 is shown upstream of the jet tube 16 and the swirl tube 17 (viewed in the flow direction of the jet tube 16 and the swirl tube 17), wherein each fuel nozzle 18 interacts with each jet tube 16 and each swirl tube 17 to introduce fuel into the respective jet tube 16 or the respective swirl tube 17 at their inlet side.

[0030] On this inlet side, combustion air can also be introduced into the jet pipe 16 and the swirl pipe 17, wherein the combustion air is initially based on Figure 1 Arrow 19, as shown, flows outward through flame tube 12 and then through flow regulator 20 in the direction of fuel nozzle 18 to flow around fuel nozzle 18, and after flowing around fuel nozzle 18, enters jet tube 16 and swirl tube 17 in its inlet region. Fuel from fuel passage 21 can be supplied to fuel nozzle 18. The combustion air flow can be balanced by flow regulator 20.

[0031] The ratio FH / FP between the area FH of the main burner 14 through which the combustion air flows and the area FP of the ignition burner 15 through which the combustion air flows is between 3 and 6, preferably between 3 and 5, particularly preferably between 3.5 and 4.5; or between 4 and 6, preferably between 4.5 and 5.5.

[0032] The area FH of the main burner 14 through which combustion air flows is obtained from the sum of the minimum cross-sectional areas of all the jet tubes 16 along their length or axial extent. Assuming all the jet tubes 16 are implemented identically, the area FH of the main burner 14 through which combustion air flows is obtained by multiplying the minimum cross-sectional area of ​​one of the jet tubes 16 by the number of jet tubes 16. The area FP of the ignition burner 15, designed as a swirl burner, through which combustion air flows, is obtained from the sum of the minimum cross-sectional areas of all the swirl tubes 17 along their length or axial extent. Assuming all the swirl tubes 17 are implemented identically, the area FP of the ignition burner 15, designed as a swirl burner, through which combustion air flows, is obtained by multiplying the minimum cross-sectional area of ​​one of the swirl tubes 17 by the number of swirl tubes 17.

[0033] The area FH of the main burner 14 through which combustion air flows and the area FP of the ignition burner 15 through which combustion air flows are the areas through which combustion air and fuel flow. Since the distribution of combustion air flow between the main burner 14 and the ignition burner 15 depends only on the ratio FH / FP, and not on the amount of fuel introduced in each case, the areas FH and FP are referred to as the areas through which combustion air flows.

[0034] Such gas turbine burners are particularly preferred for the purpose of burning both natural gas and hydrogen with full flexibility, i.e., burning both 100% natural gas and 100% hydrogen in a stable manner with low emissions, as well as any mixture of natural gas and hydrogen.

[0035] The main burner 14, designed as a jet burner, preferably has jet tubes 16 extending in a straight line between 40 and 120, particularly between 60 and 100, and especially preferably between 60 and 80. These jet tubes extend in a straight line from their inlet side to their outlet side, wherein gas and combustion air enter the jet tubes 16 in the region at the inlet side, and the mixture of fuel and combustion air exits the jet tubes 16 and enters the combustion zone 13 in the region at the outlet side.

[0036] Designed for Figure 1 The ignition burner 15 of the swirl burner specifically includes swirl tubes 17 that extend spirally or in a helical manner between 10 and 35, preferably between 15 and 30, and particularly preferably between 15 and 25.

[0037] The spiral or helical swirl tube 17 extends around the longitudinal central axis of the igniter burner 15, which preferably coincides with the longitudinal central axis of the flame tube 12.

[0038] Figure 2 A second exemplary embodiment of the gas turbine combustor 10 is shown, which is consistent with... Figure 1 The only difference of the exemplary embodiment is that the ignition burner 15, which is surrounded by the main burner 14 on the radially outer side, is not designed as a swirl burner with multiple swirl tubes 17, but is designed as a conical burner or a tapered burner.

[0039] As Figure 1 As shown in the diagram, the ignition burner 14, designed as a swirl burner, provides a swirling flow of a mixture of fuel and combustion air to the ignition burner 15, which is designed as a conical burner or a tapered burner. This swirling flow is itself introduced into the radially inner portion of the combustion zone 13 defined or bounded by the flame tube 12.

[0040] therefore, Figure 2The body 22 is shown, forming a conical section. These bodies 22 are specifically designed as conical shells with a range of approximately 90°, offset relative to each other parallel to their central axes, forming slits 23 between them. Through the slits 23, combustion air enters a hollow space radially inwardly bounded by the conical bodies 22, in which fuel can be introduced, on the one hand, via nozzles 24 and on the other hand, via fuel orifices 25. Thus, on the one hand, immediately upstream of the combustion zone 13, and therefore immediately upstream of the flame tube 12, the gas mixes with the combustion air in the region of the conical burner or tapered burner, as the fuel flows radially inward through the fuel orifices 25 into the space bounded by the bodies 22, where it mixes with the combustion air entering via the slits 23. Furthermore, fuel can be introduced upstream via nozzles 24 into the hollow space bounded by the conical bodies 22.

[0041] In the ignition burner 15, which is designed as a conical burner or a tapered burner, the area FP of the ignition burner 15 through which the combustion air flows corresponds to the minimum cross-sectional area of ​​the hollow space of the conical burner or tapered burner, which radially inner limits the body 22 of the conical burner or tapered burner, which forms a section of the cone of the conical burner or tapered burner.

[0042] Therefore, premixing of fuel and combustion air occurs in the region of the main burner 14 and in the region of the corresponding ignition burner 15. In the region of the main burner 14, this mixing occurs on the inlet side of the region of the jet tube 16, wherein the jet tube 16 then provides a mixing section for fuel and combustion air. The ratio l / d between the mixing section l of the jet tube 16 and its diameter d is preferably greater than 5, particularly preferably greater than 10. The diameter d of the jet tube 16 with the ratio l / d is the minimum diameter of the jet tube 16 along its length or axial range.

[0043] exist Figure 1 In an exemplary embodiment, premixing of fuel and combustion air also occurs in the swirl tube 17 of the ignition burner 15, which is designed as a swirl burner, such that the swirl tube 17 then provides a mixing section for fuel and combustion air, wherein the ratio l / d between the mixing section l of the swirl tube and the diameter d of the swirl tube is subsequently greater than 5, preferably greater than 10. This diameter d of the swirl tube 17 with the ratio l / d is the minimum diameter of the swirl tube 17 along its length or axial range.

[0044] exist Figure 2 In the region of the igniter 15 shown, the premixing of fuel and combustion air also occurs upstream of the combustion zone 13, that is, on the one hand, in the region of the fuel opening 25 adjacent to the upstream of the flame tube 12, and on the other hand, in the region of the nozzle 24 upstream of the flame tube 12.

[0045] exist Figure 1 and Figure 2 Of the two, a resonator chamber 26 is formed between the main burner 14 and the ignition burner 15. This resonator chamber 26 is bounded by a wall 27 and surrounds an air volume that opens via at least one resonator neck 29 with an opening 28 to the combustion zone 13 bounded by the flame tube 12. The resonator chamber 26 acts as a Helmholtz resonator and provides acoustic damping for the gas turbine burner 10. The resonator frequency depends particularly on the length of the resonator neck 29 and the size of the resonator chamber 26. Therefore, the gas turbine burner 10 can be acoustically stable, resulting in a reduced risk of damage to the gas turbine burner 10 due to thermoacoustic instability. At least one resonator neck 29 also provides cooling air to cool the burner surfaces. Features associated with the resonator chamber 26 can also be advantageously employed, independent of features on the gas turbine burner associated with the ratios FH / FP and l / d.

[0046] As already explained, fuel from fuel passage 21 can be fed to both the main burner 14 and the ignition burner 15. In the portion 21a facing the main burner 14 and the ignition burner 15, fuel passage 21 has a plate-like profile, while in the portion 21b facing away from the main burner 14 and the ignition burner 15, fuel passage 21 is formed in a roof-like or arched shape. This thus counteracts the changes in shape in the region of the fuel passage caused by thermal temperature cycling.

[0047] This can reduce the risk of unacceptably high thermal stress in the fuel passage 21, which could result in material embrittlement or plastic deformation of the fuel passage 21.

[0048] Features associated with fuel passage 21 may also be advantageously employed, while features associated with ratios FH / FP and l / d on the gas turbine combustor are irrelevant.

[0049] The main burner 14, with its jet tube 16, as well as the ignition burner 15 and fuel passage 21, can all be produced by 3D printing. This is suitable for forming conical or tapered burners. Figure 2 The ignition burner 15 and the swirl burner Figure 2 The same applies to the ignition burner 15.

[0050] The heat element is distributed to the jet tube 16 of the jet burner 14 and formed as Figure 1 The swirl tube 17 of the ignition burner 15 of the swirl burner is possible in order to detect possible backfire of the flame into the tube with the help of these thermal elements.

[0051] therefore, Figure 1 and Figure 2The gas turbine burner 10 combines a main burner 14, designed as a jet burner, with an ignition burner 15. Compared to the jet burner 14, the ignition burner 15 introduces the mixture of fuel and combustion air into the combustion zone 13 of the flame tube 12 via a swirling flow instead of a straight flow. That is, in such a way that the swirling flow of fuel and combustion air enters the radially inner region of the combustion zone 13, while the straight flow of combustion air and fuel provided by the main burner 14 enters the radially outer portion of the combustion zone 13.

[0052] Natural gas and hydrogen can both burn with high stability and low emissions (i.e., with a flexible mixing ratio between 100% hydrogen and 100% natural gas).

[0053] The fuel distribution between the main burner 14 and the ignition burner 15 is flexibly adjustable, especially between partial load operation and full load operation.

[0054] The reactor chamber 27 can be integrated into the gas turbine combustor 10 to acoustically stabilize the gas turbine combustor 10.

[0055] The fuel passage 21 of the gas turbine combustor 10 is preferably configured to avoid thermal stress as well as material embrittlement and plastic deformation of the fuel passage 21.

[0056] By integrating geometry into the main burner 14 and / or the ignition burner 15, a housing for the thermal element can be provided to enable detection of flame flashback.

[0057] List of reference numerals in the attached diagram: 10 Gas Turbine Combustor 11 Combustion Chamber 12 flame tubes 13 Combustion Zone 14 Main burner 15 Ignition Burner 16 jet tubes 17. Swirl tube 18 Fuel Injectors 19 Airflow 20 Flow regulator 21 Fuel Channel 22 body 23 Slits 24 nozzles 25 Fuel Hole 26 Resonator Chamber 27 wall 28 Opening 29. Resonator neck.

Claims

1. A gas turbine burner (10), It has a combustion chamber (11), which includes a flame tube (12), wherein, The flame tube (12) defines a combustion zone (13) of the gas turbine combustor for burning fuel in the presence of combustion air. It has a main burner (14) and an ignition burner (15), wherein the main burner (14) surrounds the ignition burner (15) radially outward. The main burner (14) is designed as a jet burner with a jet tube (16) extending in a straight line, and is configured to introduce a mixture of fuel and combustion air into the radially outer portion of the combustion zone (13) in a straight flow. The ignition burner (15) is designed as a swirl burner with a limited number of spirally or helically extending swirl tubes (17), or as a conical burner or a tapered burner, and is configured to introduce a mixture of fuel and combustion air into the radially inner portion of the combustion zone (13) by means of a swirling flow. The ratio FH / FP between the area FH of the main burner (14) through which the combustion air flows and the area FP of the ignition burner (15) through which the combustion air flows is between 3 and 6.

2. The gas turbine combustor according to claim 1, Its features are, The ratio FH / FP between the area FH of the main burner (14) through which the combustion air flows and the area FP of the ignition burner (15) through which the combustion air flows is between 3 and 5, preferably between 3.5 and 4.5; or between 4 and 6, preferably between 4.5 and 5.

5.

3. The gas turbine combustor according to claim 1 or 2, Its features are, The main burner (14) includes jet tubes (16) extending in a straight line, with between 40 and 120, preferably between 40 and 100, and particularly preferably between 60 and 80.

4. The gas turbine combustor according to any one of claims 1 to 3, Its features are, The main burner (14) is configured to mix fuel and combustion air in the inlet region of the jet tube (16) extending in a straight line. The ratio l / d between the mixing section l of the jet tube (16) and the diameter d of the jet tube (16) is greater than 5, preferably greater than 10.

5. The gas turbine combustor according to any one of claims 1 to 4, Its features are, In particular, when the ignition burner (15) is designed as a swirl burner, it includes swirl tubes (17) that extend spirally or in a helical manner between 10 and 35, preferably between 15 and 30, and particularly preferably between 15 and 25.

6. The gas turbine combustor according to any one of claims 1 to 5, Its features are, In particular, when the ignition burner (15) is designed as a swirl burner, the swirl burner is equipped to mix fuel and combustion air in the region of the swirl tube (17) in the inlet region of the swirl tube (17), wherein the ratio l / d between the mixing section l of the swirl tube (17) and the diameter d of the swirl tube (17) is greater than 5, preferably greater than 10.

7. The gas turbine combustor according to any one of claims 1 to 6, Its features are, In particular, when the ignition burner (15) is designed as a conical burner or a tapered burner, the conical burner or tapered burner is equipped to mix a first portion of the gas with combustion air immediately upstream of the flame tube (12), and to mix a second, smaller portion of the gas with combustion air further upstream of the flame tube (12).

8. The gas turbine combustor according to any one of claims 1 to 7, Its features are, A resonator chamber (26) is formed between the main burner (14) and the ignition burner (15), the resonator chamber (26) leading to the combustion zone (13) of the gas turbine burner defined by the flame tube (13).

9. The gas turbine burner according to claim 8, Its features are, The resonator chamber (26) leads to the combustion zone (13) radially defined by the flame tube (12) between the main burner (14) and the ignition burner (15).

10. The gas turbine combustor according to any one of claims 1 to 9, Its features A fuel passage (21) is provided for feeding fuel to the main burner (14) and the ignition burner (15), wherein the fuel passage (21) is designed as a plate on the portion facing the main burner (14) and the ignition burner (15), and as a roof or arch on the portion facing away from the ignition burner (15).

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