CN116878027A - Gas turbine combustion chamber nozzle structure and working method - Google Patents

Abstract

The invention relates to the technical field of gas turbines, in particular to a gas turbine combustion chamber nozzle structure and a working method thereof. The gas turbine combustor nozzle structure includes: the first cylinder wall, the second cylinder wall, the third cylinder wall, the fourth cylinder wall and the fifth cylinder wall are coaxially arranged; the hydrogen flow path is formed between the second cylinder wall and the third cylinder wall at intervals; a second-stage natural gas flow path is formed between the third cylinder wall and the fourth cylinder wall at intervals; a second air flow path is formed between the fourth cylinder wall and the fifth cylinder wall at intervals; the first-stage step is arranged at the tail ends of the second-stage natural gas flow path and the second-stage air flow path; the second-stage step is arranged at the tail end of the hydrogen flow path; the first-stage step is provided with a natural gas high-speed jet hole and a second strip-shaped air supply hole; and the secondary step is provided with a hydrogen high-speed jet hole. The nozzle structure of the combustion chamber of the gas turbine can improve the flexibility of natural gas/hydrogen mixed combustion of the gas turbine.

Description

Gas turbine combustion chamber nozzle structure and working method

Technical field

The invention relates to the technical field of gas turbines, and in particular to a gas turbine combustion chamber nozzle structure and a working method thereof.

Background technique

Gas turbines often use natural gas as fuel when used for ground power generation. When burned, they release a large amount of carbon dioxide, significantly increasing carbon emissions. Under the constraints of today's environmental protection policies and energy conservation and emission reduction, finding a clean fuel to replace traditional hydrocarbon fuels is the only way forward in the future. . At present, some gas turbine power plants use natural gas and hydrogen for mixed combustion, which has achieved the effect of reducing carbon emissions. In the future, the burner will gradually increase the proportion of hydrogen, and the carbon reduction effect will be more significant.

In order to ensure stable combustion and safety of the gas turbine, natural gas/hydrogen should be mixed evenly. Existing gas turbines that use natural gas mixed with hydrogen need to build a hydrogen mixing device outside the gas turbine body, that is, a natural gas/hydrogen mixing device. After mixing evenly, it is passed into the nozzle of the gas turbine combustion chamber; and, when the hydrogen doping ratio is determined, the hydrogen doping ratio cannot be changed during the operation of the gas turbine and cannot be adjusted in real time. The gas turbine can only continue to operate at the current hydrogen doping ratio. , until shutdown.

Therefore, the existing gas turbine natural gas/hydrogen mixed combustion has low flexibility, which is not conducive to the normal operation of the gas turbine.

Contents of the invention

Therefore, the technical problem to be solved by the present invention is to overcome the disadvantage of low flexibility of natural gas/hydrogen mixed combustion in existing gas turbines in the prior art, thereby providing a gas turbine that can improve the flexibility of natural gas/hydrogen mixed combustion. Combustion chamber nozzle structure and working method.

In order to solve the above technical problems, the gas turbine combustion chamber nozzle structure provided by the present invention includes:

The first cylinder wall, the second cylinder wall, the third cylinder wall, the fourth cylinder wall and the fifth cylinder wall are coaxially arranged;

Wherein, the outer peripheral wall of the second cylinder wall and the inner peripheral wall of the third cylinder wall form a hydrogen flow path along the radial direction; the outer peripheral wall of the third cylinder wall and the inner surface of the fourth cylinder wall A secondary natural gas flow path is formed at radial intervals between the peripheral walls; a secondary air flow path is formed at radial intervals between the outer peripheral wall of the fourth cylinder wall and the inner peripheral wall of the fifth cylinder wall;

A first step is provided at the end of the secondary natural gas flow path and the secondary air flow path; a second step is provided at the end of the hydrogen flow path; the first step is axially close to the downstream one The side is jointly enclosed with the outer peripheral wall of the fourth cylinder wall, the downstream side of the secondary step in the axial direction, the outer peripheral wall of the second cylinder wall and the inner peripheral wall of the fifth cylinder wall to form a preset Mixed area;

The first step is provided with a high-speed natural gas jet hole and a second strip-shaped air supply hole. The high-speed natural gas jet hole is suitable for connecting the secondary natural gas flow path with the premixing zone. The second The strip-shaped air supply hole is suitable for connecting the secondary air flow path with the premixing zone; a hydrogen high-speed jet hole is provided on the secondary step, and the hydrogen high-speed jet hole is suitable for connecting the hydrogen flow The road is connected to the premixing area.

Optionally, the fifth cylinder wall includes a rectifying wall surface, the rectifying wall surface includes a first contraction section and a second contraction section, the first contraction section is located in the downstream area of the first step, and the second contraction section The section is located in the downstream area of the secondary step;

The radius of the first shrinking section is r2, and r2 satisfies r2<r1, where r1 is the radius of the first step; the radius of the second shrinking section is r4, and r4 satisfies r4<r3, where r3 is The radius of the second step is r3<r1.

Optionally, a natural gas blending hole is also provided on the first step, and the natural gas blending hole is located on the side of the natural gas high-speed jet hole radially away from the third cylinder wall; the natural gas blending hole One end of the hole is connected to the secondary natural gas flow path, and the other end is connected to the premixing zone;

A hydrogen mixing hole is also provided on the secondary step, and the hydrogen mixing hole is located on the side of the hydrogen high-speed jet hole radially away from the second cylinder wall; one end of the hydrogen mixing hole is connected to The hydrogen flow path is connected, and the other end is connected with the premixing zone.

Optionally, the angle between the central axis of the natural gas mixing hole and/or the hydrogen mixing hole and the central axis of the gas turbine combustion chamber nozzle structure is α, and α satisfies 15°≤α≤60° .

Optionally, the second cylinder wall is provided with first air holes, and the distribution of the first air holes covers the premixing zone axially close to the downstream of the secondary step;

Second air holes are provided on the fifth cylinder wall, and the distribution of the second air holes covers the premixing zone axially close to the downstream of the first step.

Optionally, the inner diameter of the first air hole and/or the second air hole is d, and d satisfies 0.2mm≤d≤1.0mm.

Optionally, the central axis of the natural gas high-speed jet hole and the hydrogen high-speed jet hole are parallel to the central axis of the gas turbine combustion chamber nozzle structure;

The natural gas high-speed jet hole and the hydrogen high-speed jet hole are shrinkage holes, and the radial cross-sectional areas of the natural gas high-speed jet hole and the hydrogen high-speed jet hole gradually decrease along the jet direction;

The shrinkage ratio of the natural gas high-speed jet hole and/or the hydrogen high-speed jet hole is γ, and γ satisfies γ<3.

Optionally, a primary air flow path is formed radially apart between the outer peripheral wall of the first cylinder wall and the inner peripheral wall of the second cylinder wall;

A cyclone is provided at the outlet at the end of the primary air flow path, and the cyclone is suitable for producing a swirl flow in the gas;

The first-level air flow path is provided with a flow stabilizing portion at one end close to the cyclone in the axial direction, and a first strip-shaped air supply hole is opened in the said flow-stabilizing portion. The first strip-shaped air supply hole is suitable for to stabilize air flow.

Optionally, the inner peripheral wall of the first cylinder wall encloses a primary natural gas flow path;

A blocking portion is provided at the end of the first cylinder wall, and a natural gas jet hole is provided on the blocking portion. The injection port of the natural gas jet hole is located between two adjacent blades of the cyclone.

The working method of the gas turbine combustor nozzle structure provided by the present invention is applied to the gas turbine combustor nozzle structure as described above. The working method of the gas turbine combustor nozzle structure includes:

The natural gas supply source supplies diffused natural gas to the first-level natural gas flow path, so that the diffused natural gas is injected into the blade passage of the cyclone through the natural gas jet hole. At the same time, the compressor supplies diffusion air to the first-level air flow path, so that the diffused air passes through the second-level air flow path. A strip of air supply hole stably flows and then shoots into the blade channel of the cyclone. It is quickly mixed with the diffusion natural gas and then transferred to the flame tube and ignited by the igniter to form a diffusion combustion flame, that is, a duty flame. A stable reflux area is formed under the action of the flow device, which acts as a stable ignition source;

The compressor supplies premixed air to the secondary air flow path, and the natural gas supply source supplies premixed natural gas to the secondary natural gas flow path, so that the premixed air flows stably through the second strip-shaped air supply hole and then flows downstream of the first step. A recirculation area, that is, a step vortex, is generated in the area, and at the same time, the premixed natural gas is emitted from the natural gas blending hole and the natural gas high-speed jet hole, and is quickly mixed with the air in the step vortex and flows downstream. When the premixed air and the premixed natural gas When flowing to the secondary step, a step vortex will be generated in the area immediately downstream of the secondary step;

The hydrogen supply source supplies hydrogen to the hydrogen flow path, so that the hydrogen is transmitted from the hydrogen mixing hole and the hydrogen high-speed jet hole to the step vortex near the secondary step, and is quickly mixed with the premixed gas of natural gas and air to form natural gas, The premixed gas of hydrogen and air propagates downstream of the nozzle until it is transmitted to the flame tube, where it is ignited and burned by the duty flame.

The technical solution of the present invention has the following advantages:

1. The gas turbine combustion chamber nozzle structure provided by the present invention forms a first sudden expansion structure and a second sudden expansion structure by providing a first step and a second step, so that when the gas flows through, the first step and the second step are arranged. A recirculation area, also known as a step vortex, is generated near the second step. The turbulence in the step vortex is relatively high. Natural gas and hydrogen are continuously mixed with air in the step vortex after passing out from the step. Due to the high internal turbulence, natural gas and hydrogen are continuously mixed with air in the step vortex. , coupled with the gas reflux, the three can be quickly mixed evenly and propagated downstream to the flame tube for combustion; by setting up high-speed natural gas jet holes and hydrogen high-speed jet holes, the penetration of natural gas and hydrogen can be improved. In addition, the jet velocity is high, Based on the Bernoulli effect, the surrounding gas can be attracted to the jet beam, which is beneficial to rapid and uniform mixing. Through the above arrangement, the gas turbine combustion chamber nozzle structure of the present invention can achieve rapid and uniform mixing of natural gas, hydrogen and air without building a hydrogen mixing device outside the gas turbine body, and the hydrogen mixing ratio can be adjusted in real time during the operation of the gas turbine, thereby improving The flexibility of natural gas/hydrogen blended combustion in gas turbines. In addition, natural gas blended with hydrogen can significantly reduce carbon emissions.

2. In the gas turbine combustion chamber nozzle structure provided by the present invention, the angle α between the central axis of the natural gas mixing hole and/or the hydrogen mixing hole and the central axis of the gas turbine combustion chamber nozzle structure satisfies 15°. ≤α≤60°, which can not only improve the mixing efficiency of the gas, but also ensure the high fluidity of the gas.

3. In the gas turbine combustion chamber nozzle structure provided by the present invention, first air holes are opened on the second cylinder wall, so that the first air holes are densely distributed and cover the pre-stage near the downstream of the secondary step in the axial direction. mixing zone; and by opening second air holes on the fifth cylinder wall, so that the second air holes are densely distributed and cover the premixing zone axially close to the downstream of the first step, thereby passing through the third One air hole and the second air hole jet form an air film to prevent the combustible mixture from direct contact with the wall, thereby increasing the flow speed of the boundary layer of the mixture to be greater than the flame propagation speed, preventing the boundary layer from tempering, and at the same time Cool the wall surface and extend its service life.

4. In the gas turbine combustion chamber nozzle structure provided by the present invention, the natural gas high-speed jet hole is a shrinkage hole, and its radial cross-sectional area gradually decreases along the jet direction. The shrinkage ratio γ of the natural gas high-speed jet hole satisfies γ<3, It is beneficial to increase the speed and penetration strength of the natural gas jet. On the one hand, it can strengthen the mixing effect, and on the other hand, it can increase the overall average flow rate of the mixed gas and prevent the central flow from tempering; the hydrogen high-speed jet hole is a shrinkage hole, and its radial direction The cross-sectional area gradually decreases along the jet direction. The shrinkage ratio γ of the hydrogen high-speed jet hole satisfies γ<3, which is beneficial to increasing the hydrogen jet speed and penetration strength. On the one hand, it can enhance the mixing effect, and on the other hand, it can improve the mixing effect. The overall average flow rate of the gas is adjusted to prevent central flow backfire.

5. The working method of the gas turbine combustion chamber nozzle structure provided by the present invention generates step vortices by setting steps, which can quickly and uniformly mix natural gas/hydrogen and air. Therefore, natural gas and hydrogen can be separately supplied to the gas turbine combustion chamber. The mixture is mixed while flowing, rather than being evenly mixed before delivering the mixture to the combustion chamber. This method enables the gas turbine to independently adjust the natural gas flow and hydrogen flow during operation, so that the gas turbine can maintain stable operation despite dynamic changes in fuel flow, thereby improving the combustion flexibility of the gas turbine and ensuring safe and stable combustion of the gas turbine; Moreover, the gas turbine burning a mixture of natural gas and hydrogen can reduce carbon emissions, and as the proportion of hydrogen added increases, the environmental protection effect becomes more significant.

Description of the drawings

In order to more clearly explain the specific embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings that need to be used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description The drawings illustrate some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without exerting any creative effort.

Figure 1 is a schematic cross-sectional view of the gas turbine combustion chamber nozzle structure of the present invention;

Figure 2 is an enlarged view of point A in Figure 1;

Figure 3 is a dimensional view of the first contraction section and the second contraction section of the gas turbine combustion chamber nozzle structure of the present invention;

Figure 4 is a schematic isometric view of the gas turbine combustion chamber nozzle structure of the present invention;

Figure 5 is a schematic front structural view of the gas turbine combustion chamber nozzle structure of the present invention;

Figure 6 is a cross-sectional view of the B-B section in Figure 5;

Figure 7 is a cross-sectional view of the C-C section in Figure 5;

Figure 8 is an enlarged view of D in Figure 6;

Figure 9 is a right view of Figure 5;

Figure 10 is a schematic diagram of the working principle of the step vortex generated by the gas turbine combustion chamber nozzle structure of the present invention.

Explanation of reference symbols:

10. First cylinder wall; 100. Primary natural gas flow path; 11. Blocking part; 110. Natural gas jet hole;

20. Second cylinder wall; 200. Primary air flow path; 201. First air hole; 21. Cyclone; 22. Stabilizing part; 220. First strip air supply hole;

30. Third cylinder wall; 300. Hydrogen flow path;

40. Fourth cylinder wall; 400. Secondary natural gas flow path;

50. Fifth cylinder wall; 500. Secondary air flow path; 501. Second air hole; 51. Rectification wall; 511. First contraction section; 512. Second contraction section;

60. First step; 600. Premixed area; 601. Natural gas high-speed jet hole; 602. Natural gas blending hole; 603. Second strip air supply hole;

70. Second-level steps; 701. Hydrogen high-speed jet hole; 702. Hydrogen mixing hole.

Detailed ways

The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate The orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed in a specific orientation. and operation, and therefore cannot be construed as limitations of the present invention. Furthermore, the terms “first”, “second” and “third” are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise clearly stated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection or a detachable connection. Connection, or integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be an internal connection between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

Embodiment 1

As shown in Figures 1 to 10, the gas turbine combustion chamber nozzle structure provided in this embodiment includes:

Coaxially arranged first cylinder wall 10, second cylinder wall 20, third cylinder wall 30, fourth cylinder wall 40 and fifth cylinder wall 50;

Wherein, a hydrogen flow path 300 is formed radially apart between the outer peripheral wall of the second cylinder wall 20 and the inner peripheral wall of the third cylinder wall 30; the outer peripheral wall of the third cylinder wall 30 and the fourth The inner peripheral walls of the cylinder wall 40 are radially spaced to form a secondary natural gas flow path 400; the outer peripheral wall of the fourth cylinder wall 40 and the inner peripheral wall of the fifth cylinder wall 50 are radially spaced to form a secondary natural gas flow path 400. air flow path 500;

The first step 60 is provided at the end of the secondary natural gas flow path 400 and the secondary air flow path 500; the second step 70 is provided at the end of the hydrogen flow path 300; the first step 60 is provided along the The side axially closer to the downstream and the outer peripheral wall of the fourth cylinder wall 40, the side of the secondary step 70 axially closer to the downstream, and the outer peripheral wall of the second cylinder wall 20 and the fifth cylinder The inner peripheral walls of the wall 50 together form a premixed area 600;

The first step 60 is provided with a high-speed natural gas jet hole 601 and a second strip-shaped air supply hole 603. The high-speed natural gas jet hole 601 is suitable for connecting the secondary natural gas flow path 400 to the premixing zone 600. The second strip-shaped air supply hole 603 is suitable for connecting the secondary air flow path 500 with the premixing zone 600; a hydrogen high-speed jet hole 701 is provided on the secondary step 70. The hydrogen high-speed jet hole 701 is suitable for connecting the hydrogen flow path 300 and the premixing zone 600 .

It should be noted that the gas turbine combustor nozzle structure of the present invention is divided into an intake section, a premixing section and a diffusion section along the axial direction, wherein the premixing section of the gas turbine combustor nozzle structure is in a contracted shape as a whole. Among them, the primary natural gas flow path 100, the primary air flow path 200, the hydrogen flow path 300, the secondary natural gas flow path 400 and the secondary air flow path 500 are located in the air inlet section of the gas turbine combustion chamber nozzle structure; the first step 60. Rectification wall 51, secondary step 70, first air hole 201, second air hole 501, natural gas high speed jet hole 601, natural gas blending hole 602, second strip air supply hole 603, hydrogen high speed jet hole 701 and The hydrogen mixing hole 702 is located in the premixing section of the gas turbine combustor nozzle structure; the first strip air supply hole 220, the swirler 21 and the natural gas jet hole 110 are located in the diffusion section of the gas turbine combustor nozzle structure.

It should be noted that, please refer to Figures 1 and 4. The gas turbine combustion chamber nozzle structure includes a first cylinder wall 10, a second cylinder wall 20, a third cylinder wall 30 and a fourth cylinder wall 40 arranged coaxially. and the fifth cylinder wall 50, any phase among the first cylinder wall 10, the second cylinder wall 20, the third cylinder wall 30, the fourth cylinder wall 40 and the fifth cylinder wall 50. They are arranged radially apart between two adjacent ones. Please refer to FIG. 1 , in which a hydrogen flow path 300 is formed radially apart between the outer peripheral wall of the second cylinder wall 20 and the inner peripheral wall of the third cylinder wall 30 . A secondary natural gas flow path 400 is formed radially between the outer peripheral wall and the inner peripheral wall of the fourth cylinder wall 40 , and between the outer peripheral wall of the fourth cylinder wall 40 and the inner peripheral wall of the fifth cylinder wall 50 Secondary air flow paths 500 are formed at radial intervals.

It should be noted that, as shown in Figures 1 and 2, the first step 60 is provided at the end of the secondary natural gas flow path 400 and the secondary air flow path 500; One radial side is connected to the inner peripheral wall of the fifth cylindrical wall 50, the other side is connected to the outer peripheral wall of the third cylindrical wall 30, and the axial side of the first step 60 is connected to the third cylindrical wall 50. The ends of the four cylinder walls 40 are connected; the first step 60 forms an angle of 90 degrees with the central axis of the gas turbine combustion chamber nozzle structure to form a first sudden expansion structure, so that the air flows through the The first sudden expansion structure generates a backflow area, that is, a step vortex, in the downstream area immediately adjacent to the first step 60. The turbulence degree in the step vortex is high, and the gas inside has a reverse velocity, which in turn helps the air and The blending of natural gas improves the gas blending efficiency. The secondary step 70 is provided at the end of the hydrogen flow path 300; one radial side of the secondary step 70 is connected to the outer peripheral wall of the second cylinder wall 20, and the other side is connected to the third The ends of the barrel wall 30 are connected; the secondary step 70 forms a 90-degree angle with the central axis of the gas turbine combustion chamber nozzle structure to form a second sudden expansion structure, thereby allowing air and natural gas to flow through the second The sudden expansion structure creates a backflow area, that is, a step vortex, in the downstream area immediately adjacent to the secondary step 70. The turbulence degree in the step vortex is high, and the gas inside has a reverse velocity, which in turn helps air, natural gas and The blending of hydrogen further improves the gas blending efficiency. The downstream side of the first step 60 in the axial direction and the outer peripheral wall of the fourth cylinder wall 40 , and the downstream side of the second step 70 in the axial direction and the outer peripheral wall of the second cylinder wall 20 The peripheral wall and the inner peripheral wall of the fifth cylinder wall 50 together form a premixing zone 600, which is suitable for mixing natural gas, air and hydrogen.

Optionally, the number of the second strip-shaped air supply holes 603 is eight, and the eight second strip-shaped air supply holes 603 are evenly arranged on the first step 60 along the circumferential direction, which is beneficial to improving the The uniformity of the air jet improves the mixing uniformity and mixing efficiency of air and natural gas.

It should be noted that, still referring to FIGS. 1 and 2 , a natural gas high-speed jet hole 601 is opened on the first step 60 so that one end of the natural gas high-speed jet hole 601 is connected to the secondary natural gas flow path 400 , the other end is connected to the premixing zone 600, thereby increasing the jet velocity and penetration strength of the natural gas. On the one hand, it can enhance the mixing effect of natural gas and air, on the other hand, it can increase the overall average flow rate of the mixed gas and prevent the center flow tempering; a hydrogen high-speed jet hole 701 is opened on the secondary step 70 so that one end of the hydrogen high-speed jet hole 701 is connected to the hydrogen flow path 300 and the other end is connected to the premixing zone 600 , thereby increasing the jet velocity and penetration strength of hydrogen. On the one hand, it can enhance the mixing effect of natural gas, air and hydrogen. On the other hand, it can increase the overall average flow rate of the mixed gas and prevent central flow backfire.

In this embodiment, the first step 60 and the second step 70 are provided to form the first sudden expansion structure and the second sudden expansion structure respectively, so that when the gas flows through, the first step 60 and the second step 70 are formed. A recirculation area, that is, a step vortex, is generated near 70. The turbulence in the step vortex is high. After natural gas and hydrogen pass out from the step, they are continuously mixed with air in the step vortex. Due to the high internal turbulence, and the gas Backflow can quickly mix the three evenly and propagate downstream to the flame tube for combustion; by setting up the natural gas high-speed jet hole 601 and the hydrogen high-speed jet hole 701, the penetration of natural gas and hydrogen can be improved. In addition, the jet velocity is high, based on The Bernoulli effect can attract the surrounding gas to converge towards the jet beam, which is beneficial to rapid and uniform mixing. Through the above arrangement, the gas turbine combustion chamber nozzle structure of the present invention can achieve rapid and uniform mixing of natural gas, hydrogen and air without building a hydrogen mixing device outside the gas turbine body, and the hydrogen mixing ratio can be adjusted in real time during the operation of the gas turbine, thereby improving The flexibility of natural gas/hydrogen blended combustion in gas turbines. In addition, natural gas blended with hydrogen can significantly reduce carbon emissions.

Specifically, the fifth cylinder wall 50 includes a rectifying wall surface 51 , and the rectifying wall surface 51 includes a first shrinking section 511 and a second shrinking section 512 , and the first shrinking section 511 is located in the downstream area of the first step 60 , the second contraction section 512 is located in the downstream area of the secondary step 70;

The radius of the first shrinking section 511 is r2, and r2 satisfies r2<r1, where r1 is the radius of the first step 60; the radius of the second shrinking section 512 is r4, and r4 satisfies r4<r3, where , r3 is the radius of the secondary step 70, r3<r1.

Specifically, a natural gas mixing hole 602 is also provided on the first step 60, and the natural gas mixing hole 602 is located on the side of the natural gas high-speed jet hole 601 radially away from the third cylinder wall 30; One end of the natural gas mixing hole 602 is connected to the secondary natural gas flow path 400, and the other end is connected to the premixing zone 600;

The secondary step 70 is also provided with a hydrogen mixing hole 702. The hydrogen mixing hole 702 is located on the side of the hydrogen high-speed jet hole 701 radially away from the second cylinder wall 20; One end of the mixing hole 702 is connected to the hydrogen flow path 300 , and the other end is connected to the premixing zone 600 .

It should be noted that, as shown in FIG. 3 , the rectifying wall surface 51 is arranged on the fifth cylinder wall 50 in a constricted shape along the air flow direction. The rectifying wall surface 51 includes a first constriction section 511 and a second constriction section. 512. The first contraction section 511 is located in the downstream area of the first step 60, and the radius r2 of the first contraction section 511 is smaller than the radius r1 of the first step 60. When the premixed air flows from the second strip The air supply hole 603 spreads rapidly after passing out. Part of the premixed air flows to the vicinity of the first step 60 to generate a step vortex, and the remaining part flows downstream of the nozzle. When it flows to the rectification wall corresponding to the first contraction section 511 Collision with it causes this part of the premixed air to produce a more significant component velocity in the radial direction of the nozzle, while the natural gas emitted from the natural gas mixing hole 602 has a component velocity in the radial direction of the nozzle. Both radial velocities On the contrary, but with the same axial speed, it is conducive to the rapid mixing of air and natural gas; otherwise, if the radius r2 of the first contraction section 511 is greater than the radius r1 of the first step 60, the second strip of air will The premixed air transmitted from the supply hole 603 will not collide with the rectification wall corresponding to the first constriction section 511, or even if there is a collision, this part of the premixed air will not cause significant inward distribution along the radial direction of the nozzle. speed. Similarly, the second contraction section 512 is located in the downstream area of the secondary step 70, and the radius r4 of the second contraction section 512 is smaller than the radius r3 of the secondary step 70. In the direction of the mixture of air and natural gas, During the movement of the nozzle end, part of the mixed air flows to the vicinity of the secondary step 70 to generate a step vortex, and the remaining part flows downstream of the nozzle, and collides with the rectifying wall corresponding to the second constriction section 512 when it flows to it. , so that the mixed gas in this part produces a more significant component velocity in the radial direction of the nozzle, while the hydrogen gas emitted from the hydrogen mixing hole 702 has a component velocity in the radial direction of the nozzle, and the radial velocities of the two are opposite. However, the axial speed is the same, which is beneficial to the rapid mixing of air, natural gas and hydrogen.

It should be noted that, as shown in FIG. 1 , since the hydrogen diffusion speed is faster and the required premixing distance is shorter, in this embodiment, the axial length of the hydrogen flow path 300 is larger than the secondary natural gas. The axial length of the flow path 400 , that is, the premixing length of hydrogen is smaller than the premixing length of natural gas.

Optionally, the inner and outer bends of the rectifying wall surface 51 are rounded to reduce gas flow loss.

Specifically, the angle between the central axis of the natural gas mixing hole 602 and/or the hydrogen mixing hole 702 and the central axis of the gas turbine combustion chamber nozzle structure is α, and α satisfies 15°≤α≤60 °.

It should be noted that, please refer to Figure 2. The central axis of the gas turbine combustor nozzle structure refers to the axis pointed by the lead "L" in Figures 1 to 3, where the two clips shown in Figure 2 The central axis L of the gas turbine combustion chamber nozzle structure at the corner can be obtained based on the parallel principle and will not be described again here; the central axis of the natural gas mixing hole 602 refers to the axis pointed by the lead "P" in Figure 2 , the central axis of the hydrogen mixing hole 702 refers to the axis pointed by the lead "Q" in Figure 2, and the central axis of the natural gas mixing hole 602 and/or the hydrogen mixing hole 702 is consistent with the gas turbine. The angle between the central axes of the combustion chamber nozzle structure refers to the angle "α" in Figure 2. The included angle α cannot be too small, otherwise it will easily cause the jet component velocity of the natural gas mixing hole 602 and/or the hydrogen gas mixing hole 702 to be too small along the radial direction, and the component velocity along the axial direction to be too large. It is conducive to blending, and the jet penetration is low, which is also not conducive to blending. Therefore, the included angle α needs to satisfy α ≥ 15°; the included angle α cannot be too large, otherwise it will easily cause the natural gas to be mixed. The partial velocity of the jet in the mixing hole 602 and/or the hydrogen mixing hole 702 is too large in the radial direction, and the partial velocity in the axial direction is too small. The larger radial flow velocity will decelerate the other fluid mixed with it. , is not conducive to flow, and is also not conducive to blending. Therefore, the included angle α needs to satisfy α ≤ 60°; the central axis of the natural gas blending hole 602 and/or the hydrogen blending hole 702 and the gas turbine The angle α between the central axes of the combustion chamber nozzle structure satisfies 15°≤α≤60°, which can not only improve the mixing efficiency of the gas, but also ensure high fluidity of the gas.

Optionally, the angle α between the central axis of the natural gas mixing hole 602 and the central axis of the gas turbine combustion chamber nozzle structure is α=30°, so that the natural gas is injected obliquely into the air flow, which is beneficial to Mixing is uniform; the angle α between the central axis of the hydrogen mixing hole 702 and the central axis of the gas turbine combustion chamber nozzle structure is α=30°, thereby injecting hydrogen obliquely into the mixture of natural gas and air. , which is conducive to uniform mixing.

Specifically, the second cylinder wall 20 is provided with first air holes 201, and the distribution of the first air holes 201 covers the premixing zone 600 close to the downstream of the secondary step 70 in the axial direction;

The fifth cylinder wall 50 is provided with second air holes 501 , and the distribution of the second air holes 501 covers the premixing zone 600 close to the downstream of the first step 60 in the axial direction.

It should be noted that, as shown in FIG. 1 , the second cylinder wall 20 and the fifth cylinder wall 50 are the wall surfaces in contact with each other during the premixed flow of natural gas, hydrogen and air. First air holes 201 are opened on the second step 70 so that the first air holes 201 are densely distributed and cover the premixing zone 600 close to the downstream of the secondary step 70 in the axial direction; and by opening a third air hole 201 on the fifth cylinder wall 50 The two air holes 501 are densely distributed and cover the premixing zone 600 near the downstream of the first step 60 in the axial direction, so that the first air holes 201 and the second air holes pass through The 501 jet forms a gas film to prevent direct contact between the combustible gas mixture and the wall, thereby increasing the flow velocity of the gas mixture boundary layer to be greater than the flame propagation speed, preventing boundary layer tempering, and at the same time cooling the wall surface to extend its service life. At the same time, since the premixed section of the gas turbine combustion chamber nozzle structure is in a shrinking shape as a whole, and the natural gas high-speed jet hole 601 and the hydrogen high-speed jet hole 701 are shrinkage holes, the average flow speed of the mixed gas can be significantly increased, making it larger than the flame Propagation speed to prevent central flow backfire.

Specifically, the inner diameter of the first air hole 201 and/or the second air hole 501 is d, and d satisfies 0.2mm≤d≤1.0mm.

It should be noted that the inner diameter of the first air hole 201 and/or the second air hole 501 is d (not shown in the figure), and the inner diameter d cannot be too small, otherwise the air circulation area will easily be exceeded. Small, which limits the air flow. Therefore, the inner diameter d needs to satisfy d≥0.2mm; the inner diameter d cannot be too large, otherwise it will easily cause the air jet velocity to decrease and the penetration to weaken, which is not conducive to blending. Therefore, The inner diameter d needs to satisfy d≤1.0mm; to sum up, the inner diameter d of the first air hole 201 and/or the second air hole 501 satisfies 0.2mm≤d≤1.0mm, thus ensuring that both The air jet velocity is at a relatively fast level, which enhances the penetration of the jet and the average flow rate of the mixed air, and ensures sufficient air flow, thus improving the mixing efficiency.

Specifically, the central axes of the natural gas high-speed jet hole 601 and the hydrogen high-speed jet hole 701 are parallel to the central axis of the gas turbine combustion chamber nozzle structure;

The natural gas high-speed jet hole 601 and the hydrogen high-speed jet hole 701 are shrinkage holes, and the radial cross-sectional areas of the natural gas high-speed jet hole 601 and the hydrogen high-speed jet hole 701 gradually decrease along the jet direction;

The shrinkage ratio of the natural gas high-speed jet hole 601 and/or the hydrogen high-speed jet hole 701 is γ, and γ satisfies γ<3.

It should be noted that, as shown in Figure 2, the central axis of the natural gas high-speed jet hole 601 is parallel to the central axis of the gas turbine combustion chamber nozzle structure. The natural gas high-speed jet hole 601 is a shrinkage hole, and its radial direction The cross-sectional area gradually decreases along the jet direction. The shrinkage ratio γ of the natural gas high-speed jet hole 601 satisfies γ<3, which is conducive to increasing the natural gas jet speed and penetration strength. On the one hand, it can enhance the mixing effect, and on the other hand, it can improve The overall average flow rate of the mixed gas prevents central flow backfire; similarly, the central axis of the hydrogen high-speed jet hole 701 is parallel to the central axis of the gas turbine combustion chamber nozzle structure, and the hydrogen high-speed jet hole 701 is a shrink hole , its radial cross-sectional area gradually decreases along the jet direction. The shrinkage ratio γ of the hydrogen high-speed jet hole 701 satisfies γ<3, which is conducive to increasing the hydrogen jet speed and penetration strength. On the one hand, it can strengthen the blending effect, and on the other hand, On the one hand, it can increase the overall average flow rate of the mixed air and prevent central flow backfire.

It is worth mentioning that compared with the gas turbine combustor nozzles currently in service, the premixing section of the present invention has no swirl components, and the overall structure is more compact and concise, which significantly reduces production and processing costs, and is more conducive to maintenance and repair. replace.

Specifically, a primary air flow path 200 is formed radially apart between the outer peripheral wall of the first cylinder wall 10 and the inner peripheral wall of the second cylinder wall 20;

A cyclone 21 is provided at the outlet at the end of the primary air flow path 200, and the cyclone 21 is suitable for generating a swirl flow in the gas;

The primary air flow path 200 is provided with a flow stabilizing portion 22 at one end close to the cyclone 21 in the axial direction, and a first strip-shaped air supply hole 220 is opened in the flow stabilizing portion 22. The air supply holes 220 are suitable for stabilizing air flow.

It should be noted that, as shown in FIG. 1 , chamfering is performed on the end surface of the first-stage air flow path 200 to facilitate the flow of fresh premixed air to the recirculation area formed downstream of the cyclone 21 . It was ignited and burned by the fire on duty.

Optionally, the number of the first strip-shaped air supply holes 220 is four, and the four first strip-shaped air supply holes 220 are evenly arranged around the flow stabilizing portion 22 to stabilize the air flow.

Specifically, the inner peripheral wall of the first cylinder wall 10 encloses a primary natural gas flow path 100;

A blocking portion 11 is provided at the end of the first cylinder wall 10 , and a natural gas jet hole 110 is provided in the blocking portion 11 . The injection ports of the natural gas jet hole 110 are located on two adjacent sides of the cyclone 21 . between the leaves.

Embodiment 2

Different from the first embodiment, in this embodiment, the axial length of the hydrogen flow path 300 is equal to the axial length of the secondary natural gas flow path 400, that is, only one step is provided to form a single sudden expansion structure, so that A step vortex is formed, and the rectifying wall surface only corresponds to one contraction section, which can simplify the nozzle structure without affecting the mixing effect and make the nozzle structure more compact.

Embodiment 3

The working method of the gas turbine combustor nozzle structure provided in this embodiment is applied to the gas turbine combustor nozzle structure as described above. The working method of the gas turbine combustor nozzle structure includes:

The natural gas supply source supplies diffused natural gas to the primary natural gas flow path 100, so that the diffused natural gas is injected into the blade passage of the cyclone 21 through the natural gas jet hole 110. At the same time, the compressor supplies diffusion air to the primary air flow path 200, so that The diffusion air flows stably through the first strip-shaped air supply hole 220 and then shoots into the blade channel of the cyclone 21, and is quickly mixed with the diffusion natural gas and then transferred to the flame tube and ignited by the igniter to form a diffusion combustion flame, that is, Duty flame, and form a stable reflux area under the action of the cyclone 21, acting as a stable ignition source;

The premixed air is supplied from the compressor to the secondary air flow path 500, and the premixed natural gas is supplied from the natural gas supply source to the secondary natural gas flow path 400, so that the premixed air flows stably through the second strip air supply hole 603 and then flows in the first stage. The downstream area of the step 60 generates a recirculation area, that is, a step vortex. At the same time, the premixed natural gas is transmitted from the natural gas blending hole 602 and the natural gas high-speed jet hole 601, and is quickly mixed with the air in the step vortex and flows downstream. When the premixed natural gas is When the mixed air and premixed natural gas flow to the secondary step 70, a step vortex will be generated in the area immediately downstream of the secondary step 70;

Hydrogen is supplied from the hydrogen supply source to the hydrogen flow path 300, so that the hydrogen is transmitted from the hydrogen mixing hole 702 and the hydrogen high-speed jet hole 701 to the step vortex near the secondary step 70, and is quickly mixed with the premixed gas of natural gas and air. , forming a premixed gas of natural gas, hydrogen and air, which propagates downstream of the nozzle until it is transmitted to the flame tube, where it is ignited and burned by the duty flame.

It should be noted that in the present invention, the fuel used for duty combustion, that is, diffusion combustion, is natural gas, rather than hydrogen or a mixture of natural gas/hydrogen. The reason is that diffusion combustion is different from premixed combustion and cannot adjust the flame surface temperature. If the fuel contains In the presence of hydrogen, the flame surface temperature will increase significantly, which can easily lead to a significant increase in the emission of thermal nitrogen oxides. Therefore, when pure natural gas is used, the flame surface temperature can be kept at a low level, which can effectively control the generation of thermal nitrogen oxides.

The following is a unified description of the working method of the gas turbine combustion chamber nozzle structure of the present invention:

When the gas turbine combustion chamber nozzle structure is in operation, the diffused natural gas is injected into the blade passage of the swirler 21 through the natural gas jet hole 110, and at the same time, the diffused air flows through the first strip air supply hole 220 and then injected into the swirler 21. between the blade channels, and is quickly mixed with the diffused natural gas and then transferred to the flame tube and ignited by the igniter to form a diffused combustion flame, that is, a duty flame, and a stable reflux area is formed under the action of the cyclone 21, which acts as a stable ignition source. At the same time, the premixed air flows stably and then ejects through the second strip-shaped air supply hole 603. Due to the existence of the first step 60, the air flows through the sudden expansion structure and will be in the downstream area immediately adjacent to the first step 60. A recirculation area is generated, that is, a step vortex, as shown in Figure 10. The turbulence degree in the step vortex is high, and the gas inside has a reverse velocity; at the same time, the premixed natural gas is emitted from the natural gas blending hole 602 and the natural gas high-speed jet hole 601 , quickly mixes with the air in the step vortex and flows downstream. The high turbulence and reverse velocity in the step vortex help gas mixing, because the central axis of the natural gas blending hole 602 is consistent with the gas turbine combustor nozzle structure. The angle between the central axes is α, so that the natural gas is injected obliquely into the air flow, which is conducive to uniform mixing. The central axis of the natural gas high-speed jet hole 601 is parallel to the central axis of the gas turbine combustion chamber nozzle structure, and the natural gas high-speed jet Hole 601 is a shrink hole, which is conducive to increasing the natural gas jet velocity and penetration strength. On the one hand, it can enhance the mixing effect, and on the other hand, it can increase the overall average flow rate of the mixed gas and prevent central flow backfire. The air and natural gas continue to flow downstream of the nozzle in the rectifying wall 51. When flowing to the secondary step 70, similar to the above, a step vortex will be generated in the downstream area immediately adjacent to the secondary step 70. At the same time, hydrogen is mixed through the hydrogen mixing hole 702 and the hydrogen high-speed jet hole 701 is transmitted to the step vortex near the secondary step 70, and is quickly mixed with the premixed gas of natural gas and air to form a premixed gas of natural gas, hydrogen and air, and propagates downstream of the nozzle until the Out of the flame tube, it is ignited and burned by the duty flame; the angle between the central axis of the hydrogen mixing hole 702 and the central axis of the gas turbine combustion chamber nozzle structure is α, which can inject hydrogen obliquely into the natural gas and air. In the gas mixture, it is conducive to uniform mixing. The central axis of the hydrogen high-speed jet hole 701 is parallel to the central axis of the gas turbine combustion chamber nozzle structure, and the hydrogen high-speed jet hole 701 is a shrinkage hole, which is beneficial to increasing the jet velocity and penetration of the hydrogen. The penetration strength can, on the one hand, enhance the mixing effect, and on the other hand, it can increase the overall average flow rate of the mixed air and prevent central flow backfire.

It should be noted that the hydrogen-doped natural gas combustion scheme adopted by the gas turbine before the improvement requires that the mixing work be completed before the natural gas and hydrogen are transported to the combustion chamber, and once the hydrogen doping ratio is determined, the gas turbine cannot be changed during operation. You can only keep running with the current hydrogen doping amount. Otherwise, when the hydrogen doping amount changes for some reason and the natural gas flow rate remains unchanged, it will easily lead to unstable combustion of the gas turbine or even a shutdown. The working method of the gas turbine combustion chamber nozzle structure of the present invention generates step vortices by setting steps, which can quickly and evenly mix natural gas/hydrogen and air. Therefore, natural gas and hydrogen can be separately supplied to the gas turbine combustion chamber and mixed while flowing in the nozzle. Instead of mixing evenly, the mixture is delivered to the combustion chamber. This method enables the gas turbine to independently adjust the natural gas flow and hydrogen flow during operation, so that the gas turbine can maintain stable operation despite dynamic changes in fuel flow, thereby improving the combustion flexibility of the gas turbine and ensuring safe and stable combustion of the gas turbine; Moreover, the gas turbine burning a mixture of natural gas and hydrogen can reduce carbon emissions, and as the proportion of hydrogen added increases, the environmental protection effect becomes more significant.

Obviously, the above-mentioned embodiments are only examples for clear explanation and are not intended to limit the implementation. For those of ordinary skill in the art, other different forms of changes or modifications can be made based on the above description. An exhaustive list of all implementations is neither necessary nor possible. The obvious changes or modifications derived therefrom are still within the protection scope of the present invention.

Claims (10)

1. A gas turbine combustion chamber nozzle structure, characterized in that it includes: Coaxially arranged first cylinder wall (10), second cylinder wall (20), third cylinder wall (30), fourth cylinder wall (40) and fifth cylinder wall (50); Wherein, a hydrogen flow path (300) is formed along the radial direction between the outer peripheral wall of the second cylinder wall (20) and the inner peripheral wall of the third cylinder wall (30); the third cylinder wall (30) The outer peripheral wall of the fourth cylinder wall (40) and the inner peripheral wall of the fourth cylinder wall (40) are radially spaced to form a secondary natural gas flow path (400); the outer peripheral wall of the fourth cylinder wall (40) and the fifth cylinder wall Secondary air flow paths (500) are formed at radial intervals between the inner peripheral walls of the wall (50); A first step (60) is provided at the end of the secondary natural gas flow path (400) and the secondary air flow path (500); a second step (70) is provided at the hydrogen flow path (300) The end of the first step (60) is axially close to the downstream side and the outer peripheral wall of the fourth cylinder wall (40), and the second step (70) is axially close to the downstream side and The outer peripheral wall of the second cylinder wall (20) and the inner peripheral wall of the fifth cylinder wall (50) together form a premixed area (600); The first step (60) is provided with a natural gas high-speed jet hole (601) and a second strip-shaped air supply hole (603). The natural gas high-speed jet hole (601) is suitable for connecting the secondary natural gas flow path (601). 400) is connected with the premixing zone (600), and the second strip-shaped air supply hole (603) is suitable for connecting the secondary air flow path (500) with the premixing zone (600). ; The secondary step (70) is provided with a high-speed hydrogen jet hole (701), and the high-speed hydrogen jet hole (701) is suitable for connecting the hydrogen flow path (300) to the premixing zone (600) Pass. 2. The gas turbine combustor nozzle structure according to claim 1, characterized in that the fifth cylinder wall (50) includes a rectifying wall surface (51), and the rectifying wall surface (51) includes a first constriction section (511) and a second contraction section (512). The first contraction section (511) is located in the downstream area of the first step (60), and the second contraction section (512) is located in the downstream area of the second step (70). downstream area; The radius of the first contraction section (511) is r ₂ , and r ₂ satisfies r ₂ <r ₁ , where r ₁ is the radius of the first step (60); the second contraction section (512) The radius is r ₄ , and r ₄ satisfies r ₄ <r ₃ , where r ₃ is the radius of the secondary step (70), and r ₃ <r ₁ . 3. The gas turbine combustor nozzle structure according to claim 1, characterized in that the first step (60) is also provided with a natural gas mixing hole (602), and the natural gas mixing hole (602) is located at the The natural gas high-speed jet hole (601) is radially away from the side of the third cylinder wall (30); one end of the natural gas blending hole (602) is connected to the secondary natural gas flow path (400), The other end is connected with the premixing zone (600); The secondary step (70) is also provided with a hydrogen mixing hole (702). The hydrogen mixing hole (702) is located radially away from the second cylinder wall (701) of the hydrogen high-speed jet hole (701). 20); one end of the hydrogen mixing hole (702) is connected to the hydrogen flow path (300), and the other end is connected to the premixing zone (600). 4. The gas turbine combustor nozzle structure according to claim 3, characterized in that the central axis of the natural gas mixing hole (602) and/or the hydrogen mixing hole (702) is consistent with the gas turbine combustor nozzle. The angle between the central axes of the structure is α, and α satisfies 15°≤α≤60°. 5. The gas turbine combustion chamber nozzle structure according to claim 1, characterized in that the second cylinder wall (20) is provided with first air holes (201), and the distribution of the first air holes (201) Cover the premixing zone (600) axially close to the downstream of the secondary step (70); The fifth cylinder wall (50) is provided with second air holes (501), and the distribution of the second air holes (501) covers the premixing zone (501) close to the downstream of the first step (60) in the axial direction. 600). 6. The gas turbine combustion chamber nozzle structure according to claim 5, characterized in that the inner diameter of the first air hole (201) and/or the second air hole (501) is d, and d satisfies 0.2mm≤ d≤1.0mm. 7. The gas turbine combustor nozzle structure according to claim 1, characterized in that the central axes of the natural gas high-speed jet hole (601) and the hydrogen high-speed jet hole (701) are aligned with the gas turbine combustor nozzle structure. 's central axes are parallel; The natural gas high-speed jet hole (601) and the hydrogen high-speed jet hole (701) are shrinkage holes, and the radial cross-sectional areas of the natural gas high-speed jet hole (601) and the hydrogen high-speed jet hole (701) are along the The direction of the jet gradually decreases; The shrinkage ratio of the natural gas high-speed jet hole (601) and/or the hydrogen high-speed jet hole (701) is γ, and γ satisfies γ<3. 8. The gas turbine combustion chamber nozzle structure according to any one of claims 1 to 7, characterized in that the outer peripheral wall of the first cylinder wall (10) and the inner peripheral wall of the second cylinder wall (20) A primary air flow path (200) is formed at radial intervals; A cyclone (21) is provided at the outlet at the end of the primary air flow path (200), and the cyclone (21) is suitable for generating a swirl flow in the gas; The primary air flow path (200) is provided with a flow stabilizing portion (22) at one end close to the cyclone (21) in the axial direction, and a first strip-shaped air supply is provided on the flow stabilizing portion (22). hole (220), the first strip-shaped air supply hole (220) is suitable for stabilizing air flow. 9. The gas turbine combustor nozzle structure according to claim 8, characterized in that the inner peripheral wall of the first cylinder wall (10) encloses a primary natural gas flow path (100); A blocking part (11) is provided at the end of the first cylinder wall (10). A natural gas jet hole (110) is provided on the blocking part (11). The injection port of the natural gas jet hole (110) is located at between two adjacent blades of the swirler (21). 10. A working method of a gas turbine combustor nozzle structure, applied to the gas turbine combustor nozzle structure according to any one of claims 1 to 9, characterized in that the working method of the gas turbine combustor nozzle structure includes: : The diffused natural gas is supplied from the natural gas supply source to the primary natural gas flow path (100), so that the diffused natural gas is injected into the blade channel of the cyclone (21) through the natural gas jet hole (110), and at the same time, the diffused natural gas is injected from the compressor to the primary air flow path (200) supplies diffusion air so that the diffusion air flows stably through the first strip air supply hole (220) and then shoots between the blade channels of the cyclone (21), and is quickly mixed with the diffusion natural gas and then passed into the flame tube. It is ignited by the igniter to form a diffusion combustion flame, that is, a duty flame, and forms a stable reflux area under the action of the cyclone (21), which acts as a stable ignition source; The premixed air is supplied from the compressor to the secondary air flow path (500), and the premixed natural gas is supplied from the natural gas supply source to the secondary natural gas flow path (400), so that the premixed air passes through the second strip air supply hole (603) After the flow is stabilized, a backflow area, that is, a step vortex, is generated in the downstream area of the first step (60). At the same time, the premixed natural gas is transmitted from the natural gas blending hole (602) and the natural gas high-speed jet hole (601), and interacts with the step vortex. The air is rapidly mixed and flows downstream. When the premixed air and premixed natural gas flow to the secondary step (70), a step vortex will be generated in the downstream area immediately adjacent to the secondary step (70); Hydrogen is supplied from the hydrogen supply source to the hydrogen flow path (300), so that the hydrogen is transmitted from the hydrogen mixing hole (702) and the hydrogen high-speed jet hole (701) to the step vortex near the secondary step (70), and mixes with natural gas and The premixed gas of air is rapidly mixed to form a premixed gas of natural gas, hydrogen and air, which propagates downstream of the nozzle until it is transmitted to the flame tube, where it is ignited and burned by the duty flame.