A combustion chamber head device and ignition method for a pure hydrogen gas turbine

Abstract

This invention provides a combustion chamber head device and ignition method for a pure hydrogen gas turbine. It relates to the field of gas turbine combustion chamber design, solving the problem of unreliable ignition in existing pure hydrogen combustion chambers. The device includes: a fuel distribution component, a multi-cluster burner, and a base; the multi-cluster burner includes a central combustion cluster and multiple interconnected combustion clusters surrounding the central combustion cluster; the multiple interconnected combustion clusters are divided into N-stage combustion chambers; the fuel distribution component includes a central fuel pipe and N-stage interconnected fuel pipes; each stage of interconnected fuel pipes is isolated from each other and from the central fuel pipe; the central fuel pipe is connected to the top of the central combustion cluster; each stage of interconnected fuel pipe is connected to the top of its corresponding combustion chamber; the bottom ends of the central combustion cluster and the N-stage combustion chambers are respectively connected to the base. This invention provides reliable start-up, stable operation, and low emissions over wide loads, achieving multi-cluster interconnection and reliable flame propagation, significantly improving ignition success rate and combustion stability.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustor design, and more particularly to a head device for a pure hydrogen gas turbine combustor and an ignition and flame connection method. Background Technology

[0002] With the advancement of the "dual carbon" goal, the application of pure hydrogen and high-hydrogen fuels in gas turbines has become an important technological path to achieve deep decarbonization. Pure hydrogen fuel has extremely high flame propagation speed, extremely wide flammability limit and extremely strong reactivity, which brings a series of challenges to the combustion chamber, such as backfire, thermoacoustic oscillation and NOx emission control.

[0003] Existing pure hydrogen micro-hybrid combustion chambers mostly employ direct spark plug ignition or a separate igniter. These methods suffer from high ignition energy requirements, low ignition success rates, and limited flame propagation distance under pure hydrogen fuel conditions, making it difficult to quickly and reliably ignite multiple micro-hybrid combustion clusters. Furthermore, while existing staged combustion structures can achieve staged fuel supply, the flame connection between different combustion clusters is weak, leading to flameout or unstable combustion in some clusters at low loads. This results in poor overall combustion chamber ignition reliability, a narrow load adjustment range, and a high risk of thermoacoustic oscillations.

[0004] Therefore, a new combustion chamber structure and ignition method are urgently needed to address the key technological requirements for reliable start-up, stable operation, and low emissions over a wide range of loads in pure hydrogen gas turbine combustion chambers. Summary of the Invention

[0005] A brief overview of the invention is given below to provide a basic understanding of certain aspects of it. It should be understood that this overview is not an exhaustive summary of the invention. It is not intended to identify key or essential parts of the invention, nor is it intended to limit the scope of the invention. Its purpose is merely to present certain concepts in a simplified form as a prelude to the more detailed description that follows.

[0006] In view of this, the present invention provides a combustion chamber head device and ignition and flame connection method for a pure hydrogen gas turbine, so as to at least solve the problems of unreliable ignition of pure hydrogen combustion chamber and unstable flame connection of multiple clusters in the prior art.

[0007] According to one aspect of the present invention, a combustion chamber head device and ignition method for a pure hydrogen gas turbine are provided, comprising: a fuel distribution component, a multi-cluster burner, and a base;

[0008] The multi-cluster burner includes a central combustion cluster and multiple interconnected combustion clusters surrounding the central combustion cluster; the multiple interconnected combustion clusters are divided into N-stage combustion chambers; N is a positive integer and N≥2;

[0009] The fuel distribution component includes a central fuel pipe and N-stage tandem flame fuel pipes; each stage of tandem flame fuel pipes is isolated from each other and from the central fuel pipe.

[0010] The central fuel pipe is connected to the top of the central combustion cluster to supply pure hydrogen fuel to the central combustion cluster;

[0011] Each stage of the combined flame fuel pipe is connected to the top of the corresponding combustion chamber to supply pure hydrogen fuel to the corresponding combustion chamber;

[0012] The bottom ends of the central combustion cluster and the N-stage combustion chamber are respectively connected to the base.

[0013] In a preferred embodiment of the present invention, the number of the combined flame fuel tubes is 2, the number of the combined flame combustion clusters is 6, and they are evenly arranged on the circumference at equal distances from the central combustion cluster;

[0014] The six tandem flame combustion clusters are divided into two-stage combustion chambers; each combustion chamber includes three tandem flame combustion clusters arranged alternately.

[0015] In a preferred embodiment of the present invention, both the central combustion cluster and the tandem combustion cluster include multiple micro-mixing units. The multiple micro-mixing units of the central combustion cluster are distributed in a multi-layered concentric ring shape, with the micro-mixing units in the same layer being uniformly arranged at equal angles along the central axis of the central combustion cluster. The multiple micro-mixing units of each tandem combustion cluster are distributed in a multi-layered concentric ring shape, with the micro-mixing units in the same layer being uniformly arranged at equal angles along the central axis of the combustion cluster. The outermost layer of micro-mixing units is not arranged in a complete circle. Alternatively, all the tandem combustion clusters are arranged in a circumferentially uniform and symmetrical manner, and the outlet of each tandem combustion cluster is arranged in a multi-layered crescent shape.

[0016] In a preferred embodiment of the present invention, each micro-hybrid unit includes a fuel injector and an air mixing pipe arranged coaxially, the annular gap between the air mixing pipe and the fuel injector is a first air inlet, and a second air inlet distributed circumferentially is formed on the sidewall of the air mixing pipe.

[0017] In a preferred embodiment of the present invention, the base is provided with a premixed gas outlet channel for each micro-mixing unit; the premixed gas outlet channel is inclined relative to the central axis of the micro-mixing unit to which it is located; the premixed gas outlet channel corresponding to the tandem combustion cluster is inclined in the opposite direction to the premixed gas outlet channel corresponding to the central combustion cluster.

[0018] In a preferred embodiment of the present invention, the tilt direction of the premixed gas outlet channel corresponding to the central combustion cluster is clockwise, and the tilt direction of the premixed gas outlet channel corresponding to the tandem combustion cluster is counterclockwise.

[0019] In a preferred embodiment of the present invention, the base is provided with a plurality of air channels penetrating the base, one end of the air channel is connected to the outside, and the other end is provided with an air outlet hole on the surface of the base.

[0020] Secondly, the present invention also provides a method for ignition and flame connection at the head of a pure hydrogen gas turbine combustor, applied to the aforementioned pure hydrogen gas turbine combustor head device, the method comprising:

[0021] Pure hydrogen fuel is supplied to the central combustion cluster through the central fuel pipe, and the central combustion cluster is ignited.

[0022] When the central combustion cluster forms a stable flame, one or more combustion chambers are ignited step by step according to the application conditions of the pure hydrogen gas turbine combustion chamber head device, and the heat radiation and active groups of the central combustion cluster are used to propagate the flame, thus achieving tandem flame.

[0023] In a preferred embodiment of the present invention, the method further includes, prior to:

[0024] By injecting external air, the head device of the combustion chamber of the pure hydrogen gas turbine is purged to form a cooling gas film.

[0025] In a preferred embodiment of the present invention, the number of the tandem combustion clusters is 6, and they are evenly arranged in a circle at equal distances from the central combustion cluster.

[0026] The six tandem flame combustion clusters are divided into two combustion chambers; each combustion chamber includes three tandem flame combustion clusters arranged alternately.

[0027] The process of sequentially igniting one or more combustion chambers and utilizing the thermal radiation and active groups of the central combustion cluster to achieve tandem flame includes:

[0028] Pure hydrogen fuel is supplied to the first-stage combustion chamber through a fuel pipe connected to the first-stage combustion chamber, thereby igniting the first-stage combustion chamber.

[0029] By utilizing the thermal radiation and propagation of active groups from the central combustion cluster, a first cascade flame is formed that matches the rotational direction of the central combustion cluster.

[0030] Pure hydrogen fuel is supplied to the second-stage combustion chamber through a fuel pipe connected to the second-stage combustion chamber, thereby igniting the second-stage combustion chamber;

[0031] By utilizing the thermal radiation and active group propagation of the central combustion cluster, sequential flame propagation of all six flame clusters is achieved.

[0032] This invention, based on a central ignition and flame-coupling method, realizes a flame-coupling mechanism for the combustion chamber head of a pure hydrogen gas turbine, meeting the key technical requirements of reliable start-up, stable operation, and low emissions over wide load range in existing pure hydrogen gas turbine combustion chambers. It achieves multi-cluster flame coupling and reliable flame propagation, significantly improving ignition success rate and combustion stability.

[0033] These and other advantages of the invention will become more apparent from the following detailed description of the preferred embodiments of the invention in conjunction with the accompanying drawings. Attached Figure Description

[0034] The present invention can be better understood by referring to the description given below in conjunction with the accompanying drawings, in which the same or similar reference numerals are used throughout the drawings to denote the same or similar parts. These drawings, together with the following detailed description, are incorporated in and form part of this specification, and are used to further illustrate preferred embodiments of the invention and explain the principles and advantages of the invention. In the drawings:

[0035] Figure 1 This is a schematic diagram showing the structure of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0036] Figure 2 This is a schematic diagram showing the fuel distribution components of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0037] Figure 3 This is a front sectional view showing the fuel distribution component of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0038] Figure 4 This is a schematic diagram of a multi-cluster burner for the head assembly of a pure hydrogen gas turbine combustion chamber according to the present invention;

[0039] Figure 5 This is a front view of the micro-mixing unit of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0040] Figure 6 This is a front sectional view of the micro-mixing unit of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0041] Figure 7 This is a top view of the base of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0042] Figure 8 This is a schematic diagram illustrating the structure of another pure hydrogen gas turbine combustion chamber head device according to the present invention;

[0043] Figure 9 This is a schematic diagram of a multi-cluster burner for another pure hydrogen gas turbine combustion chamber head device according to the present invention;

[0044] Figure 10 This is a top view of the base of another pure hydrogen gas turbine combustion chamber head device according to the present invention;

[0045] Figure 11 This is a front sectional view of the base of the pure hydrogen gas turbine combustion chamber head device of the present invention;

[0046] Figure 12 This is a flowchart illustrating the ignition and flame connection method at the head of the combustion chamber of a pure hydrogen gas turbine according to the present invention;

[0047] Figure 13 This is a diagram showing the hydrogen fuel distribution in a gas turbine under different operating conditions according to the present invention;

[0048] Figure 14 This is a schematic diagram showing the base of the present invention in relation to the premixed gas swirl.

[0049] The components include: 1. Fuel distribution unit; 2. Multi-cluster burner; 3. Base; 11. Central fuel pipe; 12. First-stage tandem flame fuel pipe; 13. Second-stage tandem flame fuel pipe; 14. Central combustion cluster; 15. First-stage combustion chamber; 16. Second-stage combustion chamber; 21. Micro-mixing unit; 211. Fuel nozzle; 212. Air mixing pipe; 213. First air inlet; 214. Second air inlet; 31. Premixed gas outlet channel; 32. Air channel.

[0050] Those skilled in the art will understand that the elements in the accompanying drawings are shown for simplicity and clarity only, and are not necessarily drawn to scale. For example, the dimensions of some elements in the drawings may be enlarged relative to other elements to aid in understanding the embodiments of the invention. Detailed Implementation

[0051] Exemplary embodiments of the invention will be described below with reference to the accompanying drawings. For clarity and brevity, not all features of actual implementations are described in the specification. However, it should be understood that many implementation-specific decisions must be made in the development of any such actual embodiment to achieve the developer's specific goals, such as complying with constraints related to the system and business, and these constraints may vary depending on the implementation. Furthermore, it should be understood that while development work can be very complex and time-consuming, such development work is merely a routine task for those skilled in the art who benefit from this disclosure.

[0052] It should also be noted that, in order to avoid obscuring the invention with unnecessary details, only the device structure and / or processing steps closely related to the solution according to the invention are shown in the accompanying drawings, while other details that are not closely related to the invention are omitted.

[0053] like Figure 1 and Figure 3 As shown, an embodiment of the present invention provides a combustion chamber head device for a pure hydrogen gas turbine, comprising: a fuel distribution component 1, a multi-cluster burner 2, and a base 3;

[0054] The multi-cluster burner 2 includes a central combustion cluster 14 and multiple tandem combustion clusters surrounding the central combustion cluster 14; the multiple tandem combustion clusters are divided into N-stage combustion chambers; N is a positive integer and N≥2;

[0055] The fuel distribution component 1 includes a central fuel pipe 11 and N-stage tandem flame fuel pipes; each stage of tandem flame fuel pipes is isolated from each other and from the central fuel pipe 11.

[0056] The central fuel pipe 11 is connected to the top of the central combustion cluster 14 to supply pure hydrogen fuel to the central combustion cluster;

[0057] Each stage of the combined flame fuel pipe is connected to the top of the corresponding combustion chamber to supply pure hydrogen fuel to the corresponding combustion chamber;

[0058] The bottom ends of the central combustion cluster 14 and the N-stage combustion chamber are respectively connected to the base 3.

[0059] To address the problems of uneven air intake distribution, low fuel-air mixing efficiency, susceptibility to backfire, insufficient head cooling, and thermoacoustic oscillations in existing pure hydrogen combustor heads, the present invention provides a pure hydrogen gas turbine combustor head device comprising three main parts: a fuel distribution component 1, a multi-cluster burner 2, and a base 3. Figure 1 and Figure 3 As shown, the fuel distribution component 1, the multi-cluster burner 2, and the base 3 are connected axially to form a complete head assembly. The upper end of the multi-cluster burner 2 is connected to the fuel distribution component 1, and the lower end is connected to the base 3. The fuel distribution component 1 is located at the uppermost end and contains multiple completely isolated fuel pipes (a central fuel pipe 11 and an N-stage tandem flame fuel pipe). Pure hydrogen fuel is introduced through these independent fuel pipes. This isolation design allows for independent control of the pure hydrogen fuel without interference, providing the foundation for subsequent staged ignition and tandem flame combustion. The multi-cluster burner 2 includes a central combustion cluster 14 located at the very center of the burner and multiple tandem flame combustion clusters surrounding the central combustion cluster. The upper end of the multi-cluster burner 2 receives pure hydrogen fuel, and the lower end outputs premixed gas. The base 3 is located at the lower end of the multi-cluster burner 2 and is a key transition component connecting the burner and the combustion chamber.

[0060] In one optional embodiment of this application, the number of the combined flame fuel tubes is 2, the number of the combined flame combustion clusters is 6, and they are evenly arranged in a circle at an equal distance 14 from the central combustion cluster;

[0061] The six tandem flame combustion clusters are divided into two-stage combustion chambers; each combustion chamber includes three tandem flame combustion clusters arranged alternately.

[0062] In embodiments of the present invention, such as Figure 1 , Figure 2 and Figure 3 As shown, the multi-cluster burner 2 includes a central combustion cluster located at the center, and six tandem combustion clusters evenly distributed circumferentially at equidistant distances from the central combustion cluster. Three alternating tandem combustion clusters form a first-stage combustion chamber 15, and the remaining three alternating tandem combustion clusters form a second-stage combustion chamber 16. The first-stage tandem fuel pipe 12 is connected to the first-stage combustion chamber 15 and supplies pure hydrogen fuel to the first-stage combustion chamber 15. The second-stage tandem fuel pipe 13 is connected to the second-stage combustion chamber 16 and supplies pure hydrogen fuel to the second-stage combustion chamber 16.

[0063] In one optional embodiment of this application, such as Figure 4 As shown, both the central combustion cluster 14 and the tandem combustion cluster include multiple micro-mixing units 21. The multiple micro-mixing units 21 of the central combustion cluster 14 are distributed in multiple concentric rings, and the micro-mixing units 21 in the same layer are evenly arranged at equal angles along the central axis of the central combustion cluster 14. The multiple micro-mixing units 21 of each tandem combustion cluster are distributed in multiple concentric rings, and the micro-mixing units 21 in the same layer are evenly arranged at equal angles along the central axis of the tandem combustion cluster. The outermost micro-mixing units 21 are arranged in a non-circular arrangement.

[0064] In this embodiment of the invention, both the central combustion cluster and the tandem combustion cluster are composed of multiple layers of concentrically arranged micro-mixing units 21. The multiple layers of micro-mixing units 21 are distributed in a concentric ring shape from the inside to the outside, and the same layer of micro-mixing units 21 are uniformly arranged at equal angles along the central axis of the combustion cluster. Among them, the outermost layer of micro-mixing units 21 of the tandem combustion cluster is not arranged in a complete circle. It generates a combustion airflow path between the central combustion cluster 14 and the tandem combustion cluster through asymmetrical pore arrangement, which increases the gas temperature of the combustion cluster, enhances combustion stability, and at the same time destroys the circumferential symmetry of thermoacoustic oscillation and avoids acoustic resonance.

[0065] In one optional embodiment of this application, such as Figures 8 to 10 As shown, both the central combustion cluster 14 and the tandem combustion cluster include multiple micro-mixing units 21. The multiple micro-mixing units 21 of the central combustion cluster 14 are distributed in a multi-layered concentric ring shape. The micro-mixing units 21 in the same layer are evenly arranged at equal angles along the central axis of the central combustion cluster 14. All the tandem combustion clusters are arranged in a circumferentially uniform and symmetrical manner. The outlet of each tandem combustion cluster is arranged in a multi-layered crescent shape.

[0066] In this embodiment of the invention, each of the tandem combustion clusters includes multiple layers of micro-mixing units 21. The number of micro-mixing units 21 in each layer can be the same or different; for example, each layer includes 3 micro-mixing units 21. In another embodiment, the number of micro-mixing units 21 in each layer gradually increases from the inside out; for example, the innermost layer includes 3 micro-mixing units 21, the middle layer includes 4 micro-mixing units 21, and the outermost layer includes 5 micro-mixing units 21. The multiple layers of micro-mixing units 21 are arranged in a crescent shape, and the crescent openings of multiple tandem combustion clusters have the same direction. The tandem combustion clusters are responsible for the staged supply of fuel under different loads. The non-axisymmetric crescent-shaped combustion cluster arrangement introduces a spatial phase difference, which can avoid thermoacoustic oscillations caused by positive feedback with acoustic pressure fluctuations in the spatial dimension.

[0067] In one optional embodiment of this application, such as Figure 5 and Figure 6 As shown, each micro-mixing unit 21 includes a fuel injector 211 and an air mixing pipe 212 arranged coaxially. The annular gap between the air mixing pipe 212 and the fuel injector 211 is a first air inlet 213. A second air inlet 214 is opened on the side wall of the air mixing pipe 212 and distributed circumferentially.

[0068] In this embodiment of the invention, the micro-mixing unit 21 adopts a combination structure of fuel nozzle 211 and coaxial air mixing pipe 212, and the air is introduced in stages through an annular gap (first air inlet 213) and circumferential multi-row side holes (second air inlet 214).

[0069] In one optional embodiment of this application, such as Figure 7 and Figure 10 As shown, the base 3 is provided with a premixed gas outlet channel 31 for each micro-mixing unit 21; the premixed gas outlet channel 31 is inclined relative to the central axis of the micro-mixing unit 21 to which it is located; the premixed gas outlet channel 31 corresponding to the tandem combustion cluster is inclined in the opposite direction to the premixed gas outlet channel 31 corresponding to the central combustion cluster 14.

[0070] During combustion, the premixed gas (a mixture of pure hydrogen fuel in the fuel pipe and air from the first air inlet 213 and the second air inlet 214) exiting from the micro-mixing unit 21 enters the premixed gas outlet channel 31 of the base 3. Because the premixed gas outlet channel 31 is inclined relative to the central axis of the combustion clusters (the central combustion cluster and multiple tandem combustion clusters), the premixed gas simultaneously acquires axial tilting velocity and circumferential rotational velocity upon leaving the base, forming a strong swirling inclined jet. The swirling direction of the six circumferential tandem combustion clusters is opposite to that of the central combustion cluster. This reverse swirling coupling enhances the tandem flame propagation efficiency, significantly enhancing the mutual entrainment and heat and mass exchange between adjacent flames, making the tandem flame propagation faster and more stable.

[0071] In this embodiment of the invention, except for the premixed gas outlet channel 31 corresponding to the micro-mixing unit 21 located at the center of the combustion cluster, the premixed gas outlet channels 31 corresponding to any layer of micro-mixing units 21 distributed around the center are inclined towards the center of the combustion cluster in a clockwise or counterclockwise direction. Moreover, the inclination direction of the premixed gas outlet channels 31 corresponding to the multiple layers of micro-mixing units 21 within the same combustion cluster is the same, and the angle between them and the central axis of the combustion cluster is in the range of 15° to 20°. The inclination direction of the premixed gas outlet channels 31 corresponding to the six flame combustion clusters is opposite to that of the central combustion cluster.

[0072] In this embodiment of the invention, the six tandem flame combustion clusters are arranged in a way that each pair of adjacent clusters alternates to belong to different stages of combustion chambers. The center distance between adjacent tandem flame combustion clusters can be matched according to the head of the combustion chamber (e.g., 90mm-100mm). The distance between adjacent micro-mixing units 21 is determined according to the size of the tandem flame combustion clusters and the number of micro-mixing units 21 (e.g., 5-8mm). The positions of the tandem flame combustion clusters in different stages of combustion chambers are arranged in a circular interlaced manner. Any two adjacent tandem flame combustion clusters belong to different stages of combustion chambers, thereby forming an orderly tandem flame path of "center-adjacent-diagonal" during the ignition process, ensuring an orderly flame propagation path, and further improving the ignition success rate and combustion continuity.

[0073] In one optional embodiment of this application, the tilting direction of the premixed gas outlet channel 31 corresponding to the central combustion cluster 14 is clockwise, and the tilting direction of the premixed gas outlet channel 31 corresponding to the tandem combustion cluster is counterclockwise.

[0074] In one optional embodiment of this application, the base is provided with a plurality of air channels 32 penetrating the base, one end of the air channel 32 is connected to the outside, and the other end is provided with an air outlet hole on the surface of the base.

[0075] In embodiments of the present invention, such as Figure 11 As shown, the base 3 also has multiple air channels 32 running vertically through it, forming a multi-ring array of outlet holes on the upper surface of the base 3 for air cooling. The diameter of the air channels 32 can be 2-4 mm.

[0076] like Figure 12 As shown, this embodiment of the invention also provides a method for ignition and flame connection at the head of a pure hydrogen gas turbine combustor, applied to the aforementioned pure hydrogen gas turbine combustor head device, the method comprising:

[0077] S1. Pure hydrogen fuel is supplied to the central combustion cluster 14 through the central fuel pipe 11, and the central combustion cluster 14 is ignited.

[0078] S2. When the central combustion cluster 14 forms a stable flame, according to the application conditions of the pure hydrogen gas turbine combustion chamber head device, one or more stages of combustion chambers are ignited step by step, and the thermal radiation and active groups of the central combustion cluster 14 are used to propagate the flame to achieve tandem flame.

[0079] In this embodiment of the invention, firstly, pure hydrogen fuel is introduced into the first fuel pipe 11 to ignite the central combustion cluster 14, causing it to form a stable flame. The flame of the central combustion cluster 14 serves as an ignition source, radiating heat and active groups to multiple surrounding tandem combustion clusters. Next, depending on the application conditions, one or more stages in the N-stage tandem fuel pipe are gradually activated. The corresponding one or more stages in the N-stage combustion chamber, under the ignition effect of the flame of the central combustion cluster 14, form tandem flames, which match and enhance coupling with the flame of the central combustion cluster 14, ultimately achieving stable combustion of the central combustion cluster 14 and one or more stages in the N-stage combustion chamber.

[0080] In this embodiment of the invention, the central combustion cluster 14 can be ignited by a spark plug or a hot surface igniter. A stable flame refers to a compact, short, and bright flame that is stably attached to or anchored near the outlet of the central combustion cluster.

[0081] In an optional embodiment of this application, the method further includes:

[0082] By injecting external air, the head device of the combustion chamber of the pure hydrogen gas turbine is purged to form a cooling gas film.

[0083] In this embodiment of the invention, during startup, air ejection purging is first performed. External air is ejected through the fuel pipes (central fuel pipe and combined flame fuel pipe) to purge the head device of the pure hydrogen gas turbine combustion chamber, forming a cooling gas film to prevent backfire and preheat the combustion cluster gaps.

[0084] In one optional embodiment of this application, the number of the tandem combustion clusters is 6, and they are evenly arranged in a circle at equal distances from the central combustion cluster;

[0085] The six tandem flame combustion clusters are divided into two combustion chambers; each combustion chamber includes three tandem flame combustion clusters arranged alternately.

[0086] The process of sequentially igniting one or more combustion chambers and utilizing the thermal radiation and active groups of the central combustion cluster to achieve tandem flame includes:

[0087] Pure hydrogen fuel is supplied to the first-stage combustion chamber through a fuel pipe connected to the first-stage combustion chamber, thereby igniting the first-stage combustion chamber.

[0088] By utilizing the thermal radiation and propagation of active groups from the central combustion cluster, a first cascade flame is formed that matches the rotational direction of the central combustion cluster.

[0089] Pure hydrogen fuel is supplied to the second-stage combustion chamber through a fuel pipe connected to the second-stage combustion chamber, thereby igniting the second-stage combustion chamber;

[0090] By utilizing the thermal radiation and active group propagation of the central combustion cluster, sequential flame propagation of all six flame clusters is achieved.

[0091] In this embodiment of the invention, there are six tandem flame combustion clusters. First, pure hydrogen fuel is supplied to the central combustion cluster 14 through the central fuel pipe 11, igniting the central combustion cluster 14 and causing it to form a stable flame rotating clockwise (or counterclockwise). The flame of the central combustion cluster 14 serves as an ignition source, radiating heat and active groups to the surrounding six tandem flame combustion clusters. Then, the first-stage tandem flame fuel pipe 12 is opened, supplying fuel to the first-stage combustion chamber composed of three alternately arranged tandem flame combustion clusters. Under the ignition effect of the flame of the central combustion cluster 14, these three tandem flame combustion clusters are rapidly ignited, forming the first round of tandem flames. The flame rotation direction of these first-stage combustion chambers 15 is counterclockwise (or clockwise), matching and enhancing the coupling with the flame rotation direction of the central combustion cluster 14. Next, the second-stage tandem flame fuel pipe 13 is turned on to supply fuel to the second-stage combustion chamber composed of the remaining three alternating tandem flame combustion clusters. The second round of tandem flame is completed by utilizing the heat radiation and active group propagation of the flame of the central combustion cluster 14, as well as the flame ignited by the first-stage combustion chamber, thus realizing the sequential tandem flame propagation of all six tandem flame combustion clusters and finally achieving stable combustion of all seven combustion clusters.

[0092] In this embodiment of the invention, the outermost micro-mixing unit 21 of the tandem combustion cluster is not arranged in a complete circular pattern. Its asymmetric structure can generate stronger turbulence and lateral mixing, reduce local fuel-rich zones, and lower NO levels. X Emissions, particularly the localized fuel-rich zone, are mainly concentrated in the upper half of the multi-cluster burner in the combustion chamber. This is caused by uneven mixing of fuel and air, and the higher temperature in this area makes it prone to producing large amounts of thermal NO. X The tandem flame combustion clusters are arranged asymmetrically, forming a combustion path between the central combustion cluster and the tandem flame combustion clusters, which significantly improves the reliability and flame propagation efficiency of sequential tandem flames.

[0093] Through the specific structure and ignition method described above, this invention achieves reliable center-ignition multi-cluster combustion under pure hydrogen fuel conditions, featuring rapid ignition, stable flame propagation, and a wide load adjustment range.

[0094] The combustion chamber head device and ignition method of a pure hydrogen gas turbine in this embodiment of the invention achieve multi-cluster flame propagation and reliable flame propagation through air jet purging preheating and backfire prevention, combined with swirl design with matching swirl direction, which significantly improves ignition success rate and combustion stability.

[0095] The embodiments of the present invention utilize a fuel staged supply method in conjunction with a combined flame method to gradually activate fuel according to operating conditions and load, thereby achieving sequential combined flame and wide load regulation.

[0096] The multi-stage air mixing of the micro-mixing unit 21, combined with the flame-coupling method, improves the uniformity of the premixed gas and effectively reduces NO. X generate.

[0097] The inclined premixed gas outlet channel 31 of the base forms a swirling jet in the flame-coupling method, which enhances flame entrainment and heat and mass exchange through swirling direction matching and suppresses thermoacoustic oscillation.

[0098] The purging function of air passage 32 provides cooling in the ignition-flame method, improving the reliability of the head. Stable operation with pure hydrogen fuel is achieved while ensuring efficient combustion.

[0099] Example 1

[0100] like Figure 13 As shown, the head used in this embodiment is Figures 8-10 The head is shown. In idle (no-load state after successful gas turbine ignition but before load connection), the central combustion cluster operates, with the flame stably anchored in the central region, forming a compact, small, and bright central flare. The combustion flow rate is 0.017 kg / s, and the fuel mass fraction reaches a maximum of 1.23 × 10⁻⁶ in the central region. -2 The outer area is almost empty, and the flame does not extinguish under no-load conditions. At 30% load, the central combustion cluster and the first-stage combustion chamber (three alternating flame-arranged clusters) work together. The flame expands from the central flare to the three alternating positions on the periphery, achieving reliable propagation through the flame-arrangement and forming a zoned stable combustion zone. The combustion flow rate is 0.038 kg / s, and the fuel mass fraction exhibits a blade-like distribution in the center and periphery, significantly improving mixing uniformity. At 70% load, the fuel flow rate is 0.55 kg / s, and the fuel further diffuses into the second-stage combustion chamber, exhibiting a clear swirling mixing mode. At 100% load, the fuel flow rate is 0.072 kg / s, with full-load ignition. All combustion clusters participate in combustion, the fuel mass fraction is evenly distributed throughout the field, and swirling mixing is thorough.

[0101] Example 2

[0102] Figure 14 The streamline distribution diagrams of the downstream cross section of the combustion chamber head corresponding to slow speed and 100% load conditions respectively further reveal the flow mechanism of fuel-air mixing.

[0103] The central combustion cluster exhibits a strong central recirculation zone. Streamlines spiral from the outer periphery of the combustion chamber toward the center, forming a large-scale closed vortex core. Through a multi-scale flow structure of "large central recirculation + multiple small vortices on the periphery," efficient mixing and flame stability are achieved over a wide load range (from idle to 100%), creating feasible conditions for low-emission and high-reliability operation of hydrogen fuel cell gas turbines.

[0104] Although the invention has been described with reference to a limited number of embodiments, those skilled in the art will understand from the foregoing description that other embodiments are conceivable within the scope of the invention described herein. Furthermore, it should be noted that the language used in this specification has been chosen primarily for readability and instructional purposes, and not for the purpose of interpreting or limiting the subject matter of the invention. Therefore, many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the appended claims. The disclosure of the invention is illustrative and not restrictive, and the scope of the invention is defined by the appended claims.

Claims

1. A pure hydrogen gas turbine combustor head arrangement, characterized by, include: Fuel distribution components, multi-cluster burners, and base; The multi-cluster burner includes a central combustion cluster and multiple interconnected combustion clusters surrounding the central combustion cluster; the multiple interconnected combustion clusters are divided into N-stage combustion chambers; N is a positive integer and N≥2; The fuel distribution component includes a central fuel pipe and N-stage tandem flame fuel pipes; each stage of tandem flame fuel pipes is isolated from each other and from the central fuel pipe. The central fuel pipe is connected to the top of the central combustion cluster to supply pure hydrogen fuel to the central combustion cluster; Each stage of the combined flame fuel pipe is connected to the top of the corresponding combustion chamber to supply pure hydrogen fuel to the corresponding combustion chamber; The bottom ends of the central combustion cluster and the N-stage combustion chamber are respectively connected to the base.

2. The apparatus of claim 1, wherein, The number of the combined flame fuel tubes is 2, and the number of the combined flame combustion clusters is 6, which are evenly arranged on the circumference at equal distances from the central combustion cluster; The six tandem flame combustion clusters are divided into two-stage combustion chambers; each combustion chamber includes three tandem flame combustion clusters arranged alternately.

3. The apparatus of claim 2, wherein, Both the central combustion cluster and the tandem combustion cluster include multiple micro-mixing units. The multiple micro-mixing units of the central combustion cluster are distributed in a multi-layered concentric ring shape, and the micro-mixing units in the same layer are evenly arranged at equal angles along the central axis of the central combustion cluster. The multiple micro-mixing units of each of the tandem flame combustion clusters are distributed in a multi-layered concentric ring shape. The micro-mixing units in the same layer are evenly arranged at equal angles along the central axis of the combustion cluster. The outermost micro-mixing units are not arranged in a complete circle. Alternatively, all of the tandem flame combustion clusters are arranged in a circumferentially uniform and symmetrical manner, and the outlet of each tandem flame combustion cluster is arranged in a multi-layered crescent shape.

4. The apparatus of claim 3, wherein, Each micro-hybrid unit includes a fuel injector and an air mixing pipe arranged coaxially. The annular gap between the air mixing pipe and the fuel injector is a first air inlet, and a second air inlet is provided on the side wall of the air mixing pipe along the circumferential direction.

5. The apparatus of claim 3, wherein, The base is provided with a premixed gas outlet channel for each micro-mixing unit; the premixed gas outlet channel is inclined relative to the central axis of the micro-mixing unit to which it is located; the premixed gas outlet channel corresponding to the tandem combustion cluster is inclined in the opposite direction to the premixed gas outlet channel corresponding to the central combustion cluster.

6. The apparatus according to claim 5, characterized in that, The premixed gas outlet channel corresponding to the central combustion cluster is tilted clockwise, while the premixed gas outlet channel corresponding to the tandem combustion cluster is tilted counterclockwise.

7. The apparatus of claim 5, wherein, The base has multiple air channels that penetrate the base. One end of each air channel is connected to the outside, and the other end has an air outlet hole on the surface of the base.

8. A method of igniting a hydrogen gas turbine combustor head pilot flame, characterized by, The method, applied to the combustion chamber head device of a pure hydrogen gas turbine according to any one of claims 1-7, comprises: Pure hydrogen fuel is supplied to the central combustion cluster through the central fuel pipe, and the central combustion cluster is ignited. When the central combustion cluster forms a stable flame, one or more combustion chambers are ignited step by step according to the application conditions of the pure hydrogen gas turbine combustion chamber head device, and the heat radiation and active groups of the central combustion cluster are used to propagate the flame, thus achieving tandem flame.

9. The method of claim 8, wherein, The method is preceded by: By injecting external air, the head device of the combustion chamber of the pure hydrogen gas turbine is purged to form a cooling gas film.

10. The method of claim 8, wherein, The number of the tandem flame combustion clusters is 6, and they are evenly arranged in a circle at equal distances from the central combustion cluster. The six tandem flame combustion clusters are divided into two combustion chambers; each combustion chamber includes three tandem flame combustion clusters arranged alternately. The process of sequentially igniting one or more combustion chambers and utilizing the thermal radiation and active groups of the central combustion cluster to achieve tandem flame includes: Pure hydrogen fuel is supplied to the first-stage combustion chamber through a fuel pipe connected to the first-stage combustion chamber, thereby igniting the first-stage combustion chamber. By utilizing the thermal radiation and propagation of active groups from the central combustion cluster, a first cascade flame is formed that matches the rotational direction of the central combustion cluster. Pure hydrogen fuel is supplied to the second-stage combustion chamber through a fuel pipe connected to the second-stage combustion chamber, thereby igniting the second-stage combustion chamber; By utilizing the thermal radiation and active group propagation of the central combustion cluster, sequential flame propagation of all six flame clusters is achieved.

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