A gas turbine combustor

Abstract

The present application relates to the technical field of gas turbine, in particular to a gas turbine combustion chamber, comprising: a casing body, a combustor assembly and a flame tube assembly, the combustor assembly is formed with a three-stage combustion pipeline near one end of the flame tube assembly, wherein the three-stage combustion pipeline comprises a hydrogen fuel pipe, a main combustion stage fuel pipe and a standby fuel pipe, the hydrogen fuel pipe, the main combustion stage fuel pipe and the standby fuel pipe extend to the inside of the combustion chamber in the flame tube assembly, the hydrogen fuel pipe is annularly arranged outside the main combustion stage fuel pipe and the standby fuel pipe, one end of the hydrogen fuel pipe which deeply extends into the inside of the combustion chamber is provided with a plurality of fuel nozzles, and the plurality of fuel nozzles are annularly distributed along the axis of the combustor assembly, in the above combustion process, the hydrogen and the natural gas are two routes which do not affect each other in the flow control and the combustion flame position, and the safety of the gas turbine use is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine technology, in particular to a gas turbine combustion chamber. BACKGROUND

[0002] The gas turbine is an internal combustion engine that extracts energy from a continuous flow of compressed air that is mixed with fuel to make hot gas and then expands the gas within a turbine section, which actually produces work. The gas turbine is a typical high-tech intensive product, and the three major components of the gas turbine are the combustion chamber, the compressor and the turbine. The performance of the combustion chamber of the gas turbine will directly affect the overall performance of the gas turbine. The combustion products of the gas turbine contain NOx (nitrogen oxides), mainly including NO and NO2. These gases will affect human health and destroy ozone to form ozone holes. Therefore, how to improve the combustion efficiency and reduce the generation of harmful gases has become a problem to be solved for the gas turbine.

[0003] To solve the above problems, the gas turbine adopts the way of premixing natural gas and air to make the natural gas burn more fully. However, to solve the problem of CO2 emission, it is necessary to use carbon-free fuel containing hydrogen. However, the existing gas turbine gas combustion chamber is designed for natural gas, and the gas turbine gas combustion chamber cannot be used when the fuel is mixed with a high proportion of hydrogen. When high-activity hydrogen is used, backfire, high NOx emission and combustion shock will occur, which increases the safety hazard. SUMMARY

[0004] The present application provides a gas turbine combustion chamber for matching dual-fuel combustion to improve combustion efficiency and safety of the gas turbine.

[0005] To achieve the above purpose, the present application provides the following technical scheme:

[0006] The present application provides a gas turbine combustion chamber, which comprises a casing body, a combustor assembly and a flame tube assembly.

[0007] The combustor assembly is arranged inside the casing body and connected with the flame tube assembly. An end of the flame tube assembly away from the combustor assembly protrudes out of the casing body.

[0008] An end of the combustor assembly close to the flame tube assembly is formed with a three-stage combustion pipeline, wherein the three-stage combustion pipeline comprises a hydrogen fuel pipe, a main combustion stage fuel pipe and a standby fuel pipe. The hydrogen fuel pipe, the main combustion stage fuel pipe and the standby fuel pipe extend into the combustion chamber in the flame tube assembly. The hydrogen fuel pipe is arranged annularly outside the main combustion stage fuel pipe and the standby fuel pipe. An end of the hydrogen fuel pipe deep into the combustion chamber is provided with a plurality of fuel nozzles, and the plurality of fuel nozzles are annularly distributed along the axis of the combustor assembly.

[0009] The combustor assembly in the present application adopts three different combustion channels for combustion when burning, and natural gas and hydrogen are also provided in the three fuel pipes. The hydrogen is combusted through multiple fuel nozzles, and the multiple fuel nozzles are arranged in a circumferential direction. This design makes the fuel nozzles uniformly distribute small-volume flames in the circumferential direction, reduces NOx emission, and ensures uniform temperature distribution at the outlet of the combustion chamber. The main combustion pipe and the standby combustion pipe are only supplied with natural gas or natural gas mixed with a low proportion of hydrogen. When the hydrogen fuel flow increases, the original natural gas combustor is not affected. The excess hydrogen is sprayed out of the hydrogen combustion nozzle to work in a supplementary combustion mode. In the above combustion process, the hydrogen and the natural gas are not affected in terms of flow control and combustion flame position. When the hydrogen fuel flow increases compared with the natural gas, the problem of backfire caused by the adaptability of the combustion equipment does not occur, and the safety of the gas turbine is improved.

[0010] In addition, the hydrogen-level fuel nozzles are arranged in a circumferential direction at an outer diameter of the natural gas level, and adopt a lean diffusion half-injection mode (LDI). The injection position is located in the corner recirculation zone of the flame tube. When the combustion chamber is operated at a low load, the combustion chamber controllability can be increased, the supplementary combustion is performed in the corner recirculation zone with a lower temperature, the CO emission is reduced, and the combustion efficiency is increased.

[0011] In some embodiments, the combustor assembly further comprises a main-stage radial swirler, an axial swirler, the discharge port of the main combustion stage fuel pipe is in communication with the main-stage radial swirler, a plurality of swirler fuel holes are formed in the main-stage radial swirler, the standby fuel pipe penetrates through the main-stage radial swirler, and a plurality of standby fuel ports are formed in the standby fuel pipe. The axial swirler is arranged on the outer side wall of the part of the standby fuel pipe that protrudes out of the main-stage radial swirler. The gap formed between the axial swirler and the outer side wall of the main-stage radial swirler is used to discharge the gas inside the plurality of swirler fuel holes.

[0012] In some embodiments, the flame tube assembly comprises a flame tube body, a mounting plate, and a front conical surface plate. The flame tube body forms a combustion chamber inside for combustion. The front conical surface plate is arranged at one end of the flame tube body close to the main-stage radial swirler, and the opening direction of the front conical surface plate faces away from the main-stage radial swirler. The front conical surface plate is provided with air sleeves corresponding to the fuel nozzles. The air sleeves correspond one-to-one to the fuel nozzles. The mounting plate is mounted on the flame tube body and covers the outer side of the front conical surface plate. The mounting plate is fixedly connected to the casing body. A plurality of air inlet holes are formed in the mounting plate. A plurality of gas film holes and a plurality of mixing holes are formed in the flame tube body, and the plurality of gas film holes and the plurality of mixing holes do not interfere with each other.

[0013] In some embodiments, the primary radial swirler further comprises an outer wall surface, the axial swirler and the outer wall surface form a first step, and a plurality of air cooling holes are formed on the first step.

[0014] In some embodiments, a connection between the air sleeve and the front conical panel is a second step, an opening of the second step faces the flame tube body, one side of the front conical panel facing the flame tube body is formed with a third step near one end of the mounting plate, and the air sleeve is arranged between the second step and the third step.

[0015] In some embodiments, a gas passing channel is formed inside the outer wall surface, and a plurality of gas outlets are formed on one side of the primary radial swirler facing the casing body, each of the gas outlets is in communication with the fuel nozzle, and the gas passing channel is in communication with the hydrogen fuel pipe.

[0016] In some embodiments, the fuel nozzle has a combustion end facing the flame tube body, the combustion end is a conical end with an opening facing the hydrogen fuel pipe, or the combustion end is a conical end with an opening facing the flame tube body.

[0017] In some embodiments, a plurality of injection holes are further formed on the fuel nozzle, and the plurality of injection holes are annularly distributed along an axis of the fuel nozzle.

[0018] In some embodiments, a distance between every two adjacent fuel nozzles in the plurality of fuel nozzles is L, a diameter of the air sleeve is D, and a relationship between the L and the D satisfies: L>2.5D.

[0019] In some embodiments, an axial sub-swirler is arranged at a portion of the fuel nozzle inserted into the air sleeve.

[0020] Alternatively, a throttle plate is arranged at the portion of the fuel nozzle inserted into the air sleeve. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 A schematic diagram of an overall structure of a gas turbine combustion chamber provided by an embodiment of the present application;

[0022] Figure 2 A schematic diagram of a combustor assembly structure in a gas turbine combustion chamber provided by an embodiment of the present application;

[0023] Figure 3 An enlarged schematic diagram of a connection between a combustor assembly and a flame tube body in a gas turbine combustion chamber provided by an embodiment of the present application;

[0024] Figure 4The structure of the fuel nozzle and the air sleeve connection in the gas turbine combustion chamber is enlarged and shown schematically according to an embodiment of the present application.

[0025] Figure 5 The flame schematic diagram of the combustor assembly in the gas turbine combustion chamber is shown according to an embodiment of the present application.

[0026] Figure 6 Another angle schematic diagram of the combustor assembly in the gas turbine combustion chamber is shown according to an embodiment of the present application.

[0027] Wherein: 1-combustor assembly, 11-primary fuel pipe, 111-primary fuel hole, 12-main fuel pipe, 13-hydrogen fuel pipe, 14-combustor head flange, 15-primary radial swirler, 151-swirler fuel hole, 16-axial swirler, 17-first step, 171-air cooling hole, 18-outer wall surface, 19-fuel nozzle, 191-injection hole, 2-casing body, 21-igniter, 22-casing flange, 3-flame tube body, 31-mounting plate, 311-inlet hole, 32-front conical surface plate, 33-air sleeve, 34-cooling air film hole, 35-mixing hole, 36-combustion chamber, 37-second step, 38-third step. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative work belong to the protection scope of the present application.

[0029] Please refer to Figure 1 , Figure 2 , Figure 3 The present application provides a gas turbine combustion chamber for matching dual-fuel combustion to improve combustion efficiency and improve the safety of the gas turbine.

[0030] To achieve the above-mentioned purpose, the present application provides the following technical solutions:

[0031] The present application provides a gas turbine combustion chamber 36, comprising a casing body 2, a combustor assembly 1 and a flame tube assembly;

[0032] The combustor assembly 1 is arranged inside the casing body 2 and connected with the flame tube assembly, and the end of the flame tube assembly away from the combustor assembly 1 protrudes out of the casing body 2;

[0033] The combustor assembly 1 is formed with three-stage combustion pipelines close to one end of the flame tube assembly, wherein the three-stage combustion pipelines include a hydrogen fuel pipe 13, a main combustion stage fuel pipe and a standby fuel pipe 11, the hydrogen fuel pipe 13, the main combustion stage fuel pipe and the standby fuel pipe 11 extend to the inside of the combustion chamber 36 in the flame tube assembly, the hydrogen fuel pipe 13 is annularly arranged outside the main combustion stage fuel pipe and the standby fuel pipe 11, the hydrogen fuel pipe 13 is provided with a plurality of fuel nozzles 19 at an end deep into the inside of the combustion chamber 36, and the plurality of fuel nozzles 19 are annularly distributed along the axis of the combustor assembly 1.

[0034] The combustor assembly 1 in the present application is combusted by using three different combustion channels, and the three fuel pipes are further provided with two fuels of natural gas and hydrogen. When the fuels are combusted, the hydrogen is combusted by the plurality of fuel nozzles 19, and the plurality of fuel nozzles 19 are circumferentially arranged. This design makes the fuel nozzles 19 uniformly distribute small-volume flames in the circumferential direction, reduces NOx emission, and ensures that the temperature distribution at the outlet of the combustion chamber 36 is uniform. The main combustion pipe and the standby combustion pipe are only supplied with natural gas or natural gas mixed with a low proportion of hydrogen. When the hydrogen fuel flow increases, the original natural gas combustor will not be affected. The excess hydrogen is sprayed out of the hydrogen combustion nozzle to work in a supplementary combustion mode. In the above combustion process, the hydrogen and the natural gas are not affected in the flow control and the combustion flame position. When the hydrogen fuel flow increases compared with the natural gas, the problem of backfire caused by the adaptability of the combustion equipment does not occur, and the safety of the gas turbine is improved.

[0035] In addition, the hydrogen-stage fuel nozzles 19 are circumferentially arranged at the outer diameter of the natural gas stage, and a lean diffusion half-injection mode (LDI) is adopted. The injection position is located in the corner recirculation zone of the flame tube. When the combustion chamber 36 is operated at low load, the controllability of the combustion chamber 36 can be increased, the supplementary combustion is performed in the corner recirculation zone with low temperature, the CO emission is reduced, and the combustion efficiency is increased.

[0036] In one embodiment, please refer to Figure 1, the combustor assembly 1 further comprises a primary radial swirler 15, an axial swirler 16, the outlet of the main fuel pipe communicates with the primary radial swirler 15, a plurality of swirler fuel holes 151 are arranged on the primary radial swirler 15, the standby fuel pipe 11 penetrates through the primary radial swirler 15, and a plurality of standby fuel ports are arranged on the standby fuel pipe 11, the axial swirler 16 is arranged on the outer side wall of the part of the standby fuel pipe 11 which protrudes out of the primary radial swirler 15, and the gap formed between the axial swirler 16 and the outer side wall of the primary radial swirler 15 is used for discharging the gas inside the plurality of swirler fuel holes 151, in the above structure, when the combustor assembly of the present application burns in the combustion chamber 36, the fuel first flows out of the standby fuel ports 111 on the cylindrical surface of the standby fuel pipe 11, at the same time, the fuel is driven by the axial swirler 16 and rotates at the outlet position of the standby fuel pipe 11, so that the fuel after rotating by the axial swirler 16 is more diffused, further stabilizing the flame, and the outlet position of the main fuel pipe 12 is provided with the primary radial swirler 15, and the plurality of blades of the primary radial swirler 15 have a cylindrical fuel passage inside, after the fuel from the main fuel pipe 12 enters the cylindrical fuel passage inside the blade, the fuel flows out of the primary radial swirler 15 and is premixed with air, ensuring normal combustion of the flame.

[0037] In one embodiment, referring to Figure 3 , Figure 4The flame tube assembly comprises a flame tube body 3, a mounting plate 31, and a front cone surface 32 plate. The flame tube body 3 is internally formed with a combustion chamber 36 for combustion. The front cone surface 32 plate is arranged at one end of the flame tube body 3 close to the main-stage radial swirler 15, and the opening direction of the front cone surface 32 plate faces away from the main-stage radial swirler 15. The front cone surface 32 plate is provided with air sleeves 33 corresponding to the fuel nozzles 19. The air sleeves 33 correspond one-to-one to the fuel nozzles 19. The mounting plate 31 is mounted to the flame tube body 3 and covers the outer side of the front cone surface 32 plate. The mounting plate 31 is fixedly connected to the casing body 2. The mounting plate 31 is provided with a plurality of air inlet holes 311. The flame tube body 3 is provided with a plurality of film holes and a plurality of mixing holes 35, and the plurality of film holes and the plurality of mixing holes 35 do not interfere with each other. In the above structure, the combustion chamber 36 of the present application is arranged in the interior of the flame tube body 3. The flame tube body 3 is mainly used for fuel combustion. The air sleeves 33 are arranged on the front cone surface 32 plate. The air sleeves 33 are arranged on the outer side of the fuel nozzles 19. The air sleeves 33 have bent edges at the inlets to reduce pressure loss. Air enters the annular channel between the fuel nozzles 19 and the air sleeves 33 and flows in the axial direction. The air is semi-diffusion mixed with hydrogen in the vertical direction. The mixed gas enters the front cone surface 32 plate and is combusted in the flame tube body 3. At the same time, the flame tube body 3 of the present application is used as a flame container. The front cone surface 32 plate at the head of the flame tube body 3 is circumferentially perforated and is provided with a plurality of air sleeves 33 corresponding to the number of holes. The number of air sleeves 33 corresponds to the number of hydrogen fuel nozzles 19. Cooling film holes 34 and mixing holes 35 are arranged on the outer side of the flame tube body 3. Air inlet holes 311 are arranged on the mounting plate 31. Air required by the combustor enters the interior of the combustor assembly 1 through the air inlet holes 311 on the mounting plate 31. The multiple rows of circular holes of the air inlet holes 311 can reduce the pulsation of air pressure flow, absorb energy, and reduce the damage of combustion shock. The number of air inlet holes 311 can adjust the air intake ratio of the combustor to the air intake of the cooling film holes 34 and the mixing holes 35 of the flame tube body 3, so as to ensure normal combustion of the fuel.

[0038] In an embodiment, the gas turbine combustor 36 further comprises a casing flange 22 arranged on the casing body 2 and used for cooperating with the combustor head flange 14, and an igniter 21 penetrating through the casing body 2 and the flame tube body 3 in sequence and extending into the interior of the flame tube body 3. The combustor assembly 1 further comprises the combustor head flange 14 fixedly connected with the casing body 2. The hydrogen fuel pipe 13, the pilot fuel pipe 11 and the main fuel pipe 12 all penetrate through the mounting flange and extend into the interior of the flame tube body 3. The igniter 21 is used for igniting the fuel in the interior of the combustor 36. The casing body 2 and the combustor assembly 1 can be fixed by bolts. The casing body 2 is provided with the casing flange 22. The combustor assembly 1 is provided with the combustor head flange 14. The combustor head flange 14 is further used for limiting the hydrogen fuel pipe 13, the pilot fuel pipe 11 and the main fuel pipe 12. During the fixing, the bolts penetrate through the combustor head flange 14 and the casing flange 22 in sequence. The mounting plate 31 is also located between the combustor head flange 14 and the casing flange 22 and is used for fixing the flame tube body 3. The stability of the overall structure of the application is improved.

[0039] In an embodiment, please refer to Figure 5 The main-stage radial swirler 15 further comprises an outer wall surface 18. The axial swirler 16 and the outer wall surface 18 are formed with a first step 17. A plurality of air cooling holes 171 are arranged on the first step 17. The first step 17 is arranged between the axial swirler 16 and the outer wall surface 18. The first step 17 is used for forming a small backflow area, so as to stabilize the combustion of the flame. In addition, dozens of air cooling holes 171 are uniformly arranged on the front end of the first step 17 in the circumferential direction. The air cooling holes 171 are used for reducing the high-temperature damage of the pilot flame to the first step 17. The number of the holes can be used to control and adjust the proportion of the air passing through the cooling holes 171 and the axial swirler 16.

[0040] In an embodiment, please refer to Figure 5 The connection between the air sleeve 33 and the front conical surface 32 plate is a second step 37. The opening of the second step 37 faces the flame tube body 3. The side of the front conical surface 32 plate facing the flame tube body 3 is formed with a third step 38 close to one end of the mounting plate 31. The air sleeve 33 is arranged between the second step 37 and the third step 38. The fuel nozzle 19 is arranged between the second step 37 and the third step 38. The second step 37 is the connection between the air sleeve 33 and the front conical surface 32 plate. The third step 38 is the side of the front conical surface 32 plate facing the flame tube body 3. Therefore, the inner and outer edges of the hydrogen flame generated by the fuel nozzle 19, the main flame generated by the main-stage radial swirler 15 and the pilot flame generated by the axial swirler 16 can be stabilized near the combustor outlet by the backflow areas generated by the three steps. The specific flame shape and the step backflow area flow field are shown in Figure 5, Figure 5 Only for an example of the flame of the present application.

[0041] In an embodiment, the outer wall surface 18 is internally provided with a gas passage, and the gas passage is provided with a plurality of gas outlets on the side of the main radial swirler 15 towards the casing body 2, each gas outlet is in communication with the fuel nozzle 19, and the gas passage is in communication with the hydrogen fuel pipe 13. In the above structure, the present application provides the fuel nozzle 19 on the outer wall surface 18, and the outer wall surface 18 is internally provided with a gas passage for conveying hydrogen. In actual use, the number of hydrogen fuel pipes 13 can be changed according to actual needs, which is not limited in the present application.

[0042] In an embodiment, the fuel nozzle 19 is further provided with a plurality of injection holes 191, and the plurality of injection holes 191 are annularly distributed along the axis of the fuel nozzle 19. The injection holes 191 are used for injecting hydrogen fuel, and the annular distribution of the plurality of injection holes 191 along the axis of the fuel nozzle 19 can ensure uniform hydrogen injection and improve the stability of combustion.

[0043] In an embodiment, the diameter of the injection hole 191 is 0.5-1.2mm. The present application controls the hydrogen flame volume generated by a single injection hole 191. The fuel nozzle 19 is provided with a maximum of 4-12 injection holes 191 on the cylindrical surface. The above design prevents the excessive number of holes from causing the flames to merge to form a larger volume of flame, and ensures that the hydrogen of the present application can be injected in a lean semi-diffusion mode.

[0044] In an embodiment, the fuel nozzle 19 has a combustion end towards the flame tube body 3. The combustion end is a tapered end opening towards the hydrogen fuel pipe 13, or the combustion end is a tapered end opening towards the flame tube body 3. In the above structure, the fuel nozzle 19 of the present application can be provided as a tapered end opening towards the hydrogen fuel pipe 13 or a tapered end opening towards the flame tube body 3 according to actual needs. The injection holes 191 are uniformly arranged on the tapered end. The present application can also directly insert the hydrogen fuel pipe 13 into the air sleeve 33, and the hydrogen is directly injected into the combustion chamber 36, which is not limited in the present application.

[0045] In an embodiment, the portion of the fuel nozzle 19 inserted into the air sleeve 33 is provided with an axial split swirler.

[0046] Alternatively, the portion of the fuel nozzle 19 inserted into the air sleeve 33 is provided with a throttle plate. The purpose of the above design is also to ensure uniform diffusion of hydrogen.

[0047] In an embodiment, please refer to Figure 6The distance between each adjacent two of the plurality of fuel nozzles 19 is L, and the diameter of the air sleeve 33 is D, and the relationship between L and D satisfies: L>2.5D. With the above spacing, the excessive fuel nozzles 19 arrangement and the too small fuel nozzle 19 spacing are prevented, the flame formed by the plurality of fuel nozzles 19 is avoided to form a continuous flame, the flame volume is increased to cause the NOx emission to increase.

[0048] In an embodiment, the fuel nozzle 19 has a first end close to the flame tube body 3, and the distance L1 between the first end and the front cone 32 plate satisfies the following relationship: L1=0±2mm, and the size of the corner recirculation zone in the fuel nozzle 19 is further controlled to control the flame shape generated by the fuel nozzle 19.

[0049] Obviously, various modifications and variations of the present application can be made by those skilled in the art without departing from the spirit and scope of the application. Thus, it is intended that the present application cover modifications and variations of this application provided they come within the scope of the appended claims and their equivalents.

Claims

1. A gas turbine combustion chamber, characterized in that, include: Casing body, burner assembly and flame tube assembly; The burner assembly is disposed inside the casing body and connected to the flame tube assembly, with one end of the flame tube assembly protruding from the casing body away from the burner assembly; The burner assembly has a three-stage combustion pipeline formed at one end near the flame tube assembly. The three-stage combustion pipeline includes a hydrogen fuel pipeline, a main combustion stage fuel pipeline, and a standby fuel pipeline. The hydrogen fuel pipeline, the main combustion stage fuel pipeline, and the standby fuel pipeline extend into the combustion chamber of the flame tube assembly. The hydrogen fuel pipeline is arranged in a ring outside the main combustion stage fuel pipeline and the standby fuel pipeline. A plurality of fuel nozzles are provided at one end of the hydrogen fuel pipeline that extends into the combustion chamber, and the plurality of fuel nozzles are distributed in a ring along the axis of the burner assembly. The flame tube assembly includes a front cone panel, which is provided with an air sleeve corresponding to each of the fuel nozzles. The outlet of the fuel nozzle is located inside the air sleeve, so that hydrogen gas is semi-diffused and mixed with air inside the air sleeve before being injected into the combustion chamber.

2. The gas turbine combustion chamber according to claim 1, characterized in that, The burner assembly also includes a main-stage radial cyclone and an axial cyclone. The outlet of the main-stage fuel pipe is connected to the main-stage radial cyclone. The main-stage radial cyclone has multiple cyclone fuel holes. The standby fuel pipe passes through the main-stage radial cyclone and has multiple standby fuel ports. The axial cyclone is located on the outer wall of the portion of the standby fuel pipe that protrudes from the main-stage radial cyclone. The gap formed between the axial cyclone and the outer wall of the main-stage radial cyclone is used to discharge gas from the multiple cyclone fuel holes.

3. The gas turbine combustion chamber according to claim 2, characterized in that, The flame tube assembly includes a flame tube body, a mounting plate, and a front conical panel. The flame tube body has a combustion chamber for combustion. The front conical panel is located at one end of the flame tube body near the main stage radial vortex, and the opening direction of the front conical panel is away from the main stage radial vortex. The mounting plate is mounted on the flame tube body and covers the outside of the front conical panel. The mounting plate is fixedly connected to the casing body. The mounting plate has multiple air inlets. The flame tube body has multiple film gas holes and multiple mixing holes, and the multiple film gas holes and multiple mixing holes do not interfere with each other.

4. The gas turbine combustion chamber according to claim 2, characterized in that, The main stage radial cyclone also includes an outer wall surface, and the axial cyclone and the outer wall surface form a first step, on which a plurality of air cooling holes are provided.

5. The gas turbine combustion chamber according to claim 3, characterized in that, The connection between the air sleeve and the front conical panel is a second step, the opening of the second step faces the flame tube body, the front conical panel faces the flame tube body on one side, and a third step is formed at the end near the mounting plate, and the air sleeve is disposed between the second step and the third step.

6. The gas turbine combustion chamber according to claim 4, characterized in that, An air passage is provided inside the outer wall surface, and the air passage forms multiple air outlets on the side of the main stage radial cyclone facing the casing body. Each air outlet is connected to the fuel nozzle, and the air passage is connected to the hydrogen fuel pipe.

7. The gas turbine combustion chamber according to claim 2, characterized in that, The fuel nozzle has a combustion end facing the flame tube body, the combustion end being a conical end with an opening facing the hydrogen fuel pipe, or the combustion end being a conical end with an opening facing the flame tube body.

8. The gas turbine combustion chamber according to claim 7, characterized in that, The fuel nozzle is also provided with multiple nozzle holes, which are distributed in a ring along the axis of the fuel nozzle.

9. The gas turbine combustion chamber according to claim 3, characterized in that, The distance between any two adjacent fuel nozzles in the plurality of fuel nozzles is L, and the diameter of the air sleeve is D. The relationship between L and D satisfies: L > 2.5D.

10. The gas turbine combustion chamber according to claim 9, characterized in that, An axial vortex divider is provided at the portion of the fuel nozzle that is inserted into the air sleeve; Alternatively, a throttle plate may be provided at the portion of the fuel nozzle that inserts into the air sleeve.

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