Combustion organization method for a gas turbine combustion chamber head arrangement and combustion chamber head arrangement

Abstract

This invention discloses a combustion organization method and combustion chamber head device for a gas turbine combustor, relating to the technical field of gas turbine combustion. It solves the problems of uneven fuel-air mixing, excessive nitrogen oxide emissions, and localized high temperatures in existing combustion chamber head devices. The device consists of a fuel distributor, fuel injection pipe, igniter, and flame tube cover. The fuel distributor internally forms a primary, secondary, and tertiary fuel distribution chamber, which are not interconnected, meaning the fuel is axially distributed in three stages. Each swirl inlet is connected to a fuel distribution chamber via a fuel injection pipe. This invention, employing a multi-stage fuel distribution and swirl inlet structure, improves fuel-air mixing, effectively avoids localized high fuel concentrations, thereby reducing localized high temperatures, lowering nitrogen oxide emissions, and achieving stable combustion of hydrogen fuel across a wide load range.

Description

Technical Field

[0001] This invention relates to the technical field of gas turbine combustion, and more particularly to a combustion organization method and a combustion chamber head device for a gas turbine combustion chamber. Background Technology

[0002] With increasingly stringent global carbon emission regulations, gas turbines are gradually transitioning from natural gas fuels to low-carbon and zero-carbon fuels. Hydrogen fuel, with its combustion product being only water, is considered a core technology for achieving carbon neutrality in gas turbines. However, the laminar flame velocity of hydrogen fuel is approximately 7-10 times that of natural gas, its quenching distance is only one-third that of natural gas, and its adiabatic flame temperature is higher. These characteristics directly lead to a significant increase in the risk of backfire and spontaneous combustion in hydrogen combustion chambers, insufficient fuel-air mixing uniformity, and difficulties in ignition and stable combustion at low loads. In response to the characteristics of hydrogen fuel, domestic and international research institutions have conducted extensive designs for combustion chamber head devices. Patent 202410734696.4 invented a pure hydrogen low-emission micro-mixing gas turbine combustion chamber, employing a staged structure with a primary and secondary head, achieving fuel-air premixing through multiple micro-mixing tube arrays. However, since all stages of fuel use a premixed mode, backfire is prone to occur under low-load conditions. Patent 202310058970.6 invented a low-emission hydrogen fuel micro-hybrid combustor, which controls the flame shape by dividing the premixed flame into multiple diffusion-type micro-hybrid flames, but the fuel supply is not designed in stages for varying operating conditions. Patent 202511056735.0 invented a pure hydrogen gas turbine combustor, which has multiple nozzle assemblies and cooling components at the head, but the igniter is still arranged on the side wall, which limits the ignition reliability. Summary of the Invention

[0003] In view of the problems of uneven mixing of fuel and air, excessive nitrogen oxides in the combustion chamber, and local high temperature phenomenon in the existing combustion chamber head device, the purpose of this invention is to provide a combustion organization method and combustion chamber head device for gas turbine combustion chamber head device.

[0004] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0005] A combustion organization method for a gas turbine combustor head device, wherein the combustor head device is configured to perform three-stage axial staged combustion, the staged combustion method comprising: under startup conditions, only the first fuel pipe 41 corresponding to the first stage fuel distribution chamber 44 is fed with hydrogen fuel and ignited by the igniter 3 to form an initial standby flame; under transition conditions, the second fuel pipe 42 corresponding to the second stage fuel distribution chamber 45 is fed with hydrogen fuel and ignited by the initial standby flame to form a premixed flame in the main combustion zone; under full load conditions, the third fuel pipe 43 corresponding to the third stage fuel distribution chamber 46 is fed with hydrogen fuel to form a supplementary combustion zone to control the outlet temperature distribution.

[0006] A combustion chamber head device for a hydrogen gas turbine, applicable to the above-mentioned combustion organization method, comprising: a flame tube cover plate 1, a fuel injection pipe 2, an igniter 3, and a fuel distributor 4, wherein the flame tube cover plate 1 and the fuel distributor 4 are connected via the fuel injection pipe 2.

[0007] The fuel distributor 4 includes: a flange cover plate, which has a primary fuel distribution chamber 44, a secondary fuel distribution chamber 45 and a tertiary fuel distribution chamber 46. The igniter 3 is located in the primary fuel distribution chamber 44 and is mounted on the flange cover plate through the igniter flange hole 31 on it. The lower end of the igniter 3 protrudes from the middle of the flame tube cover plate 1.

[0008] The fuel injection pipe 2 includes: multiple primary fuel injection pipes 21, multiple secondary fuel injection pipes 22 and multiple tertiary fuel injection pipes 23. The upper ends of the multiple primary fuel injection pipes 21 are all connected to the primary fuel distribution chamber 44, the upper ends of the multiple secondary fuel injection pipes 22 are all connected to the secondary fuel distribution chamber 45, and the upper ends of the multiple tertiary fuel injection pipes 23 are all connected to the tertiary fuel distribution chamber 46.

[0009] The flame tube cover plate 1 is provided with a plurality of first swirl air inlets 11, a plurality of second swirl air inlets 12 and a plurality of third swirl air inlets 13. Each first swirl air inlet 11 is connected to the lower end of a first-stage fuel injection pipe 21, each second swirl air inlet 12 is connected to the lower end of a second-stage fuel injection pipe 22, and each third swirl air inlet 13 is connected to the lower end of a third-stage fuel injection pipe 23.

[0010] The aforementioned hydrogen gas turbine combustion chamber head device includes a fuel distributor 4 that further comprises a first fuel pipe 41, a second fuel pipe 42, and a third fuel pipe 43. The first fuel pipe 41, the second fuel pipe 42, and the third fuel pipe 43 are all connected to a flange cover plate. The first fuel pipe 41 is connected to a primary fuel distribution chamber 44, the second fuel pipe 42 is connected to a secondary fuel distribution chamber 45, and the third fuel pipe 43 is connected to a tertiary fuel distribution chamber 46.

[0011] In the aforementioned hydrogen gas turbine combustion chamber head device, the primary fuel distribution chamber 44 is along the axis of the flange cover and passes through the flange cover; the secondary fuel distribution chamber 45 and the tertiary fuel distribution chamber 46 are arranged in upper and lower layers and both surround the primary fuel distribution chamber 44.

[0012] In the aforementioned hydrogen gas turbine combustion chamber head device, a plurality of first swirl air inlets 11 located on the flame tube cover plate 1 are arranged in a ring-shaped layer from the inside to the outside, and the plurality of first swirl air inlets 11 in each layer are arranged at equal angles around the axis of the fuel distributor 4.

[0013] The aforementioned hydrogen gas turbine combustion chamber head device includes multiple second swirl inlet holes 12 located on the flame tube cover plate 1, which are divided into at least three groups. The multiple groups of second swirl inlet holes 12 are arranged at equal angles around the axis of the fuel distributor 4.

[0014] The multiple third swirl air inlets 13 located on the flame tube cover plate 1 are divided into at least three groups, and the multiple groups of third swirl air inlets 13 are arranged at equal angles around the axis of the fuel distributor 4.

[0015] In the aforementioned hydrogen gas turbine combustion chamber head device, a third swirl inlet 13 is provided between any two adjacent sets of second swirl inlets 12.

[0016] In the aforementioned hydrogen gas turbine combustion chamber head device, the plurality of first swirl inlet holes 11, the plurality of second swirl inlet holes 12 and the plurality of third swirl inlet holes 13 are all inclined at an angle to the horizontal direction.

[0017] In the aforementioned hydrogen gas turbine combustion chamber head device, the plurality of second swirl inlets 12 in each group are arranged in a non-closed annular array; the plurality of third swirl inlets 13 in each group are arranged in a non-closed annular array, as detailed in [link to details]. Figure 3 .

[0018] Specifically, the nozzle clusters formed by the secondary fuel swirl orifice 12 and the tertiary fuel swirl orifice 13 are all distributed in a non-closed annular array; each nozzle cluster contains several circumferentially arranged nozzles, and there are notches with a preset angle between adjacent circumferential nozzles.

[0019] The notches of the nozzle clusters face the radial inner side of the flame tube cover plate 1, so that each nozzle cluster has a C-shaped or fan-shaped structure in the planar projection.

[0020] The aforementioned hydrogen gas turbine combustion chamber head assembly includes multiple flange bolt holes 47 along the outer periphery of the flange cover plate; the first fuel pipe 41 is an L-shaped bend, with its lower end connected to the side wall of the primary fuel distribution chamber 44; the second fuel pipe 42 and the third fuel pipe 43 are both straight pipes, with the lower end of the second fuel pipe 42 connected to the top side of the secondary fuel distribution chamber 45, and the lower end of the third fuel pipe 43 connected to the top side of the tertiary fuel distribution chamber 46; and flange interfaces are provided at the top ends of the first fuel pipe 41, the second fuel pipe 42, and the third fuel pipe 43.

[0021] The present invention, by employing the above-mentioned technology, has the following positive effects compared with the prior art:

[0022] (1) The present invention adopts a three-stage fuel distribution, dividing hydrogen fuel into three independent controllable channels: the first stage, the second stage, and the third stage. The first stage maintains the equivalence ratio in the easy-ignition range of 0.6 to 1.0 under ignition and low-load conditions. The second stage is put into operation at medium and high loads, and the combustion temperature is controlled by a lean premixed mode. The third stage dynamically compensates when the load rises rapidly or the fuel calorific value fluctuates. Through the optimization of the staged input sequence and flow distribution, stable combustion at 15% to 100% load rate is achieved.

[0023] (2) This invention employs a swirling air intake structure. The swirling air intake holes on the flame tube cover are obliquely cut, and the intake jet forms a rotating shear layer at the head of the flame tube. The three-stage fuel injection direction forms a 67.3° angle with the swirling air intake direction. By utilizing the entrainment effect of the high-speed swirling airflow, the size of the fuel jet is reduced, and the mixing non-uniformity is significantly reduced, thus suppressing the generation of local high-temperature hot spots from the source. The dual effect of strong mixing and shortened flame residence time greatly reduces NOx emissions at the combustion chamber outlet.

[0024] (3) The present invention adopts axial center ignition. The igniter is set at the axial center of the combustion chamber, directly facing the core of the low-speed backflow zone naturally formed by the swirling flow field. The flow velocity in this area is only 1 / 5 to 1 / 3 of the mainstream velocity, and the turbulence intensity is moderate. After the flame core is generated, it will not be blown out by the high-speed airflow. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the structure of a hydrogen gas turbine combustion chamber head device according to the present invention.

[0026] Figure 2 yes Figure 1 Cross-sectional view of the head assembly of the combustion chamber.

[0027] Figure 3 This is a schematic diagram of the structure of the flame tube cover plate of the combustion chamber head device of a hydrogen gas turbine according to the present invention.

[0028] Figure 4 This is a schematic diagram of the structure of a fuel distributor in the combustion chamber head device of a hydrogen gas turbine according to the present invention.

[0029] In the attached diagram: 1. Flame tube cover; 11. First swirl inlet; 12. Second swirl inlet; 13. Third swirl inlet; 2. Fuel injection pipe; 21. First-stage fuel injection pipe; 22. Second-stage fuel injection pipe; 23. Third-stage fuel injection pipe; 3. Igniter; 31. Igniter flange hole; 4. Fuel distributor; 41. First fuel pipe; 42. Second fuel pipe; 43. Third fuel pipe; 44. First-stage fuel distribution chamber; 45. Second-stage fuel distribution chamber; 46. Third-stage fuel distribution chamber; 47. Flange bolt hole. Detailed Implementation

[0030] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, but this is not intended to limit the scope of the invention.

[0031] Please refer to Figures 1 to 4 As shown, a hydrogen gas turbine combustion chamber head assembly includes:

[0032] Flame tube cover 1 is located at the outlet of fuel injection pipe 2 and can be connected to the flame tube head;

[0033] Fuel injection pipe 2 is located between fuel distributor 4 and flame tube cover plate 1, and is divided into primary fuel injection pipe 21, secondary fuel injection pipe 22 and tertiary fuel injection pipe 23;

[0034] Igniter 3 is located at the axial center of fuel distributor 4 and flame tube cover plate 1;

[0035] Fuel distributor 4 is located at the inlet of fuel injection pipe 2 and connected to igniter 3;

[0036] The fuel distributor 4 is provided with a first fuel pipe 41, a second fuel pipe 42 and a third fuel pipe 43. The interior of the fuel distributor 4 forms a primary fuel distribution chamber 44, a secondary fuel distribution chamber 45 and a tertiary fuel distribution chamber 46. At the outlet of the fuel distributor 4, multiple primary fuel injection pipes 21 are connected to the primary fuel distribution chamber 44, multiple secondary fuel injection pipes 22 are connected to the secondary fuel distribution chamber 45, and multiple tertiary fuel injection pipes 23 are connected to the tertiary fuel distribution chamber 46. The flame tube cover plate 1 is provided with multiple first swirl inlet holes 11, second swirl inlet holes 12 and third swirl inlet holes 13. Multiple primary fuel injection pipes 21 are connected to multiple first swirl inlet holes 11, multiple secondary fuel injection pipes 22 are connected to multiple second swirl inlet holes 12, and multiple tertiary fuel injection pipes 23 are connected to multiple third swirl inlet holes 13.

[0037] Furthermore, in a preferred embodiment, the primary fuel distribution chamber 44 is located in the central region of the fuel distributor 4, the centerline of the primary fuel distribution chamber 44 is the axis of the fuel distributor 4 and runs through the entire fuel distributor 4, the secondary fuel distribution chamber 45 is the first layer region of the fuel distributor 4 and reaches the outlet region through a pipe, and the tertiary fuel distribution chamber 46 is the second layer region of the fuel distributor 4.

[0038] Furthermore, in a preferred embodiment, the igniter 3 is located at the center of the fuel distributor 4 and the flame tube cover plate 1. Its upper flange and the flange at the center of the fuel distributor 4 have flange holes evenly distributed in the circumference, and the two can be fixed with bolts. The end of the igniter 3 extends through to the bottom of the flame tube cover plate 1.

[0039] Furthermore, in a preferred embodiment, the fuel distributor 4 has flange bolt holes 47 evenly distributed circumferentially for mounting bolts to fix the flange cover to the small cylinder.

[0040] Furthermore, in a preferred embodiment, a plurality of primary fuel injection pipes 21 are distributed circumferentially along the outlet of the fuel distributor 4, while the remaining secondary fuel injection pipes 22 and tertiary fuel injection pipes 23 are arranged around the axis of the fuel distributor 4.

[0041] Furthermore, in a preferred embodiment, the plurality of first swirl inlet holes 11 are all tangential first inlet holes at 67.3° with the horizontal axis, the plurality of second swirl inlet holes 12 are all tangential second inlet holes at 67.3° with the horizontal axis, and the plurality of third swirl inlet holes 13 are all tangential third inlet holes at 67.3° with the horizontal axis. The center line of the first swirl inlet holes 11 distributed circumferentially is the axis of the flame tube cover plate 1, and the center lines of the second swirl inlet holes 12 and the third swirl inlet holes 13 distributed circumferentially surround the axis of the flame tube cover plate 1.

[0042] A combustion organization method using a combustion chamber head device of a hydrogen gas turbine, wherein the combustion chamber head device is configured to perform three-stage axial staged combustion, the staged combustion method including: under startup conditions, only the first fuel pipe 41 corresponding to the first stage fuel distribution chamber 44 is fed with hydrogen fuel and ignited by the igniter 3 to form an initial standby flame; under transition conditions, the second fuel pipe 42 corresponding to the second stage fuel distribution chamber 45 is fed with hydrogen fuel and ignited by the initial standby flame to form a premixed flame in the main combustion zone; under full load conditions, the third fuel pipe 43 corresponding to the third stage fuel distribution chamber 46 is fed with hydrogen fuel to form a supplementary combustion zone to control the outlet temperature distribution.

[0043] The above are merely preferred embodiments of the present invention and are not intended to limit the implementation methods and protection scope of the present invention.

[0044] In addition to the above, the present invention also has the following embodiments:

[0045] In a further embodiment of the present invention, the present invention discloses a combustion chamber head device for a hydrogen gas turbine, which consists of a fuel distributor 4, a fuel injection pipe 2, an igniter 3, and a flame tube cover plate 1. The fuel distributor 4 is provided with a first fuel pipe 41, a second fuel pipe 42, and a third fuel pipe 43. The fuel distributor 4 has a primary fuel distribution chamber 44, a secondary fuel distribution chamber 45, and a tertiary fuel distribution chamber 46 inside. The three chambers are not interconnected, that is, the fuel is axially divided into three stages for delivery. The fuel distributor 4 is equipped with multiple primary fuel injection pipes 21 connected to the primary fuel distribution chamber 44, multiple secondary fuel injection pipes 22 connected to the secondary fuel distribution chamber 45, and multiple tertiary fuel injection pipes 23 connected to the tertiary fuel distribution chamber 46. The flame tube cover plate 1 is equipped with three-stage swirling air inlets, namely a first swirling air inlet 11, a second swirling air inlet 12, and a third swirling air inlet 13. The multiple primary fuel injection pipes 21 are connected to the multiple first swirling air inlets 11, the multiple secondary fuel injection pipes 22 are connected to the multiple second swirling air inlets 12, and the multiple tertiary fuel injection pipes 23 are connected to the third swirling air inlet 13. An igniter 3 is located at the axial center of the fuel distributor 4 and the flame tube cover plate 1. This invention, by employing a multi-stage fuel distribution and swirling air inlet structure, can improve the mixing effect of fuel and air, effectively avoid the existence of local high fuel concentration, thereby reducing local high temperature phenomena, reducing nitrogen oxide emissions, and achieving stable combustion of hydrogen fuel under wide loads. In addition, a method for organizing combustion in the combustion chamber of a hydrogen gas turbine is also provided.

[0046] In a further embodiment of the present invention, reference is made to Figures 1 to 4As shown, the combustion head structure of the hydrogen gas turbine of the present invention includes: a flame tube cover plate 1, a fuel injection pipe 2, an igniter 3, and a fuel distributor 4. The fuel distributor 4 is a flange cover plate. The central area of ​​this component is a primary fuel distribution chamber 44. Below the flange cover plate are two layers: a first layer is a secondary fuel distribution chamber 45, and a second layer is a tertiary fuel distribution chamber 46. Above the flange cover plate are a first fuel pipe 41, a second fuel pipe 42, and a third fuel pipe 43. The first fuel pipe 41 connects to the primary fuel distribution chamber 44, the second fuel pipe 42 connects to the secondary fuel distribution chamber 45, and the third fuel pipe 43 connects to the tertiary fuel distribution chamber 46. Each of the three fuel pipes also has six 9mm flange bolt holes 47 for easy installation and fixing. The fuel injection pipe 2 is connected to the tail end of the fuel distributor 4. The primary fuel injection pipe 21 connects to the primary fuel distribution chamber 44, the secondary fuel injection pipe 22 connects to the secondary fuel distribution chamber 45, and the tertiary fuel injection pipe 23 connects to the tertiary fuel distribution chamber 46. The flame tube cover 1 is located at the outlet of the fuel injection pipe 2, and has multiple first swirl inlet holes 11, second swirl inlet holes 12, and third swirl inlet holes 13. The igniter 3 is located at the center of the fuel distributor 4 and the flame tube cover 1, and its upper flange is fixed to the flange at the center of the fuel distributor 4 with bolts. The end of the igniter 3 extends to the bottom of the flame tube cover 1.

[0047] In a further embodiment of the present invention, fuel can be injected into the first fuel pipe 41, the second fuel pipe 42, and the third fuel pipe 43 as needed, and then flow through the primary fuel distribution chamber 44, the secondary fuel distribution chamber 45, and the tertiary fuel distribution chamber 46 respectively to reach the fuel injection pipe 2. Finally, the fuel is evenly sprayed out from each fuel injection pipe and forms a swirling flow under the action of the tangential air inlet of the flame tube cover plate 1, thereby greatly reducing the mixing non-uniformity, suppressing the generation of local high-temperature hot spots from the source and reducing the emission of nitrogen oxides.

[0048] In further embodiments of the present invention, such as Figure 1 , Figure 2 and Figure 4 As shown, the center of the first fuel pipe 41 in the fuel distributor 4 is not located on the central axis, but enters horizontally from the side in the form of a bent pipe. The second fuel pipe 42 and the third fuel pipe 43 both enter axially. The primary fuel distribution chamber 44, the secondary fuel distribution chamber 45, and the tertiary fuel distribution chamber 46 in the fuel distributor 4 are not interconnected. The primary fuel distribution chamber 44 runs through the entire fuel distributor 4 with the center as the axis. The secondary fuel distribution chamber 45 is the first layer of the fuel distributor 4. After entering the first layer, the secondary fuel enters the bottom of the fuel distributor 4 through a circular pipe. The tertiary fuel distribution chamber 46 is the second layer of the fuel distributor 4. The tertiary fuel enters the second layer of the fuel distributor 4 through a circular pipe.

[0049] In further embodiments of the present invention, such as Figure 2and Figure 3 As shown, the flame tube cover plate 1 is 230mm in size. There are 25 primary fuel injection pipes 21, distributed circumferentially around the center of the flame tube cover plate 1. The inner diameter of each fuel injection pipe is 1-3mm, and the outer diameter is 2.5-6mm. The distance between the inner and outer rings is 7mm. The number of secondary and tertiary fuel injection pipes 22 and 23 is the same, each divided into 3 groups of 35 pipes. The span between multiple groups of secondary and tertiary fuel injection pipes 22 and 23 is 120°, and the span between multiple groups of secondary and tertiary fuel injection pipes 22 and 23 is 60°. The tangential angle of the first swirl inlet 11, the second swirl inlet 12, and the third swirl inlet 13 in the flame tube cover plate 1 is the same, 67.3°, and the size of the inlet is 6mm.

[0050] In a further embodiment of the present invention, the present invention also provides a combustion organization method for a hydrogen gas turbine combustor head device, wherein the combustor head device is subjected to three-stage axial staged combustion. Under startup conditions, hydrogen fuel is introduced into the first fuel pipe 41 and ignited by the igniter 3 to form an initial standby flame. Under transition conditions, fuel is introduced into the second fuel pipe 42 and ignited by the initial standby flame to form a premixed flame in the main combustion zone. Under full load conditions, fuel is introduced into the third fuel pipe 43 to form a supplementary combustion zone to control the outlet temperature distribution.

[0051] In a further embodiment of the present invention, the hydrogen gas turbine combustor head device and its combustion organization method provided by the present invention employ a three-stage fuel distribution, dividing the hydrogen fuel into three independent controllable channels: a first stage, a second stage, and a third stage. The first stage maintains the equivalence ratio within the easily ignited range of 0.6 to 1.0 under ignition and low-load conditions; the second stage is introduced at medium to high loads, using a lean premixed mode to control the combustion temperature; and the third stage dynamically compensates for rapid load increases or fluctuations in fuel calorific value. Through optimization of the staged introduction timing and flow distribution, stable combustion is achieved at 15% to 100% load rates. A swirl-flow intake structure is adopted, with the swirl-flow intake hole of the flame tube cover plate 1 using an oblique cut structure, forming a rotating shear layer at the flame tube head from the intake jet. The three-stage fuel injection direction forms a 67.3° angle with the swirl-flow intake direction, utilizing the entrainment effect of the high-speed swirl airflow to reduce the fuel jet size and significantly reduce mixing unevenness, suppressing the generation of local high-temperature hot spots from the source. The dual effects of strong mixing and shortened flame residence time greatly reduce NOx emissions at the combustor outlet. Axial center ignition is employed, with the igniter 3 positioned at the axial center of the combustion chamber, directly opposite the core of the low-speed backflow zone naturally formed by the swirling flow field. The flow velocity in this region is only 1 / 5 to 1 / 3 of the mainstream velocity, and the turbulence intensity is moderate, ensuring that the flame core will not be extinguished by the high-speed airflow after generation. This invention develops a combustion chamber head device specifically for hydrogen fuel, systematically solving the problems of backfire suppression, blending homogenization, and stable combustion under wide operating conditions through an integrated and coordinated design of fuel distribution, intake swirl, and ignition position.

[0052] The above are merely preferred embodiments of the present invention and are not intended to limit the implementation methods and protection scope of the present invention. Those skilled in the art should recognize that any equivalent substitutions and obvious changes made based on the description and illustrations of the present invention should be included within the protection scope of the present invention.

Claims

1. A combustion organization method for a gas turbine combustor head arrangement, characterized by, The combustion chamber head device is configured to perform three-stage axial staged combustion, and the staging manner comprises: in a starting working condition, only a first fuel distribution cavity (44) corresponding first fuel pipe (41) is put into hydrogen fuel, ignited by an igniter (3), to form an initial duty flame; in a transition working condition, a second fuel distribution cavity (45) corresponding second fuel pipe (42) is put into hydrogen fuel, ignited by the initial duty flame, to form a main combustion zone premixed flame; in a full load working condition, a third fuel distribution cavity (46) corresponding third fuel pipe (43) is put into hydrogen fuel, to form a supplementary combustion zone, so as to control the outlet temperature distribution.

2. A hydrogen gas turbine combustor head arrangement adapted for use with the combustion organization method of claim 1, characterized by, Comprise: a flame tube cover plate (1), a fuel injection pipe (2), an igniter (3) and a fuel distributor (4), the flame tube cover plate (1) and the fuel distributor (4) are connected through the fuel injection pipe (2); the fuel distributor (4) comprises: a flange cover plate, a first fuel distribution cavity (44), a second fuel distribution cavity (45) and a third fuel distribution cavity (46) are arranged in the flange cover plate, the igniter (3) is arranged in the first fuel distribution cavity (44) and is installed on the flange cover plate through an igniter flange hole (31) on the first fuel distribution cavity (44), and a lower end of the igniter (3) penetrates through a middle part of the flame tube cover plate (1); the fuel injection pipe (2) comprises: a plurality of first fuel injection pipes (21), a plurality of second fuel injection pipes (22) and a plurality of third fuel injection pipes (23), upper ends of the plurality of first fuel injection pipes (21) are in communication with the first fuel distribution cavity (44), upper ends of the plurality of second fuel injection pipes (22) are in communication with the second fuel distribution cavity (45), and upper ends of the plurality of third fuel injection pipes (23) are in communication with the third fuel distribution cavity (46); a plurality of first rotational flow inlet holes (11), a plurality of second rotational flow inlet holes (12) and a plurality of third rotational flow inlet holes (13) are arranged on the flame tube cover plate (1), each first rotational flow inlet hole (11) is in communication with a lower end of a first fuel injection pipe (21), each second rotational flow inlet hole (12) is in communication with a lower end of a second fuel injection pipe (22), and each third rotational flow inlet hole (13) is in communication with a lower end of a third fuel injection pipe (23).

3. The hydrogen gas turbine combustor head apparatus of claim 2, wherein, The fuel distributor (4) further comprises: a first fuel pipe (41), a second fuel pipe (42) and a third fuel pipe (43), the first fuel pipe (41), the second fuel pipe (42) and the third fuel pipe (43) are connected with the flange cover plate, the first fuel pipe (41) is in communication with the first fuel distribution cavity (44), the second fuel pipe (42) is in communication with the second fuel distribution cavity (45), and the third fuel pipe (43) is in communication with the third fuel distribution cavity (46).

4. The hydrogen gas turbine combustor head apparatus of claim 3, wherein, The first fuel distribution cavity (44) is arranged along the axis of the flange cover plate and penetrates through the flange cover plate; the second fuel distribution cavity (45) and the third fuel distribution cavity (46) are arranged in layers and surround the first fuel distribution cavity (44).

5. The hydrogen gas turbine combustor head apparatus of claim 3, wherein, Multiple first swirl air inlets (11) located on the flame tube cover plate (1) are arranged in a ring-shaped layer from the inside to the outside, and multiple first swirl air inlets (11) in each layer are arranged at equal angles around the axis of the fuel distributor (4).

6. The hydrogen gas turbine combustor head apparatus of claim 3, wherein, The multiple second swirl inlet holes (12) located on the flame tube cover plate (1) are divided into at least three groups, and the multiple groups of second swirl inlet holes (12) are arranged at equal angles around the axis of the fuel distributor (4); Multiple third swirl air inlets (13) located on the flame tube cover plate (1) are divided into at least three groups, and multiple groups of third swirl air inlets (13) are arranged at equal angles around the axis of the fuel distributor (4).

7. The hydrogen gas turbine combustor head apparatus of claim 6, wherein, A third swirl inlet (13) is provided between any two adjacent sets of second swirl inlets (12).

8. The hydrogen gas turbine combustor head apparatus of claim 7, wherein, Multiple first swirl inlet holes (11), multiple second swirl inlet holes (12) and multiple third swirl inlet holes (13) are all inclined at an angle to the horizontal direction.

9. The hydrogen gas turbine combustor head apparatus of claim 6, wherein, The multiple second swirl inlets (12) of each group are arranged in a non-closed annular array; the multiple third swirl inlets (13) of each group are arranged in a non-closed annular array.

10. The hydrogen gas turbine combustor head apparatus of claim 3, wherein, Multiple flange bolt holes (47) are provided along the outer periphery of the flange cover plate; the first fuel pipe (41) is an L-shaped bend, and the lower end of the first fuel pipe (41) is connected to the side wall of the primary fuel distribution chamber (44); the second fuel pipe (42) and the third fuel pipe (43) are both straight pipes, the lower end of the second fuel pipe (42) is connected to the top side of the secondary fuel distribution chamber (45), and the lower end of the third fuel pipe (43) is connected to the top side of the tertiary fuel distribution chamber (46); the top ends of the first fuel pipe (41), the second fuel pipe (42) and the third fuel pipe (43) are all provided with flange interfaces.

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