Combustion chamber air conditioning apparatus for a hydrogen fuel gas turbine

Abstract

The application discloses a combustion chamber air adjusting device of a hydrogen fuel gas turbine, and relates to the technical field of gas turbine combustion chambers, which comprises a compression chamber, one end of which is provided with an air inlet; a combustion chamber fixed at one end of the compression chamber away from the air inlet; a turbine chamber fixed at one end of the combustion chamber away from the compression chamber, and a plurality of injection ports are arranged between the combustion chamber and the turbine chamber; wherein an air flow channel is formed in the combustion chamber, a plurality of adjusting components are uniformly fixed in the air flow channel, one end of the adjusting component extends into the injection port, the adjusting component and the injection port are sealed by an isolation ring, one end of the adjusting component away from the injection port penetrates the combustion chamber and is fixed with a fuel cylinder, the fuel cylinder is fixed obliquely with the combustion chamber, and the adjusting component is coaxially arranged with the fuel cylinder.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustion chamber technology, specifically to an air conditioning device for the combustion chamber of a hydrogen fuel gas turbine. Background Technology

[0002] Hydrogen fuel is characterized by its rapid flame propagation, wide combustible range, and high adiabatic flame temperature. This makes the traditional gas turbine combustion chamber structure extremely prone to backfire when burning a high proportion or even pure hydrogen fuel. The flame quenching distance of hydrogen fuel is much shorter than that of hydrocarbon fuels, making it highly susceptible to flame propagation back towards the nozzle and even the fuel supply system, burning critical components. Furthermore, NO... x Emissions control is difficult; high-temperature flames are thermal NOx generators. x The main reason for NO generation is that the high-temperature characteristics of hydrogen combustion make it necessary to control NO while ensuring combustion stability. x Emissions are extremely difficult, and combustion is unstable. The high reactivity of hydrogen fuel is easily coupled with pressure fluctuations in the combustion chamber, inducing high-frequency combustion oscillations and affecting the safe operation of the unit.

[0003] Traditional air conditioning methods (such as single swirl diffusers or simple cooling vents) are insufficient for achieving precise and dynamic management of the aerodynamic and temperature fields in the combustion zone, and cannot simultaneously suppress backfire and reduce NO. x The multiple requirements of stable combustion.

[0004] To address the above problems, the present invention provides an air conditioning device for the combustion chamber of a hydrogen fuel cell gas turbine, thereby solving the aforementioned problems. Summary of the Invention

[0005] To achieve the above objectives, the present invention provides the following technical solution: an air conditioning device for the combustion chamber of a hydrogen fuel cell gas turbine, comprising: The air compressor chamber has an air inlet at one end; The combustion chamber is fixed at the end of the compressor chamber away from the air inlet. A turbine chamber is fixed at the end of the combustion chamber away from the compressor chamber, and multiple injection ports are provided between the combustion chamber and the turbine chamber; The combustion chamber has an airflow channel inside, and multiple adjusting components are evenly fixed around the circumference of the airflow channel. One end of the adjusting component extends into the injection port, and the adjusting component and the injection port are sealed by an isolation ring. The end of the adjusting component away from the injection port passes through the combustion chamber and is fixed with a fuel cartridge. The fuel cartridge is fixed at an angle to the combustion chamber, and the adjusting component is coaxially arranged with the fuel cartridge.

[0006] Further, preferably, the adjustment component includes: A guide tube is fixed on the combustion chamber and located in the air flow channel. A conical tube is provided at one end of the guide tube away from the fuel cylinder. Multiple air inlets are provided on the conical tube for receiving the compressed air from the compressor chamber. The flame tube is coaxially fixed inside the guide tube; The main gas injection head is fixed at the axial position of the fuel cylinder, and one end extends into the flame tube; Multiple auxiliary gas injection heads are configured and evenly distributed around the main gas injection head, and fixed to the fuel cylinder. One end of each auxiliary gas injection head extends into the flame cylinder.

[0007] Further, preferably, the flame tube includes: The premixing section is coaxially fixed inside the guide tube by multiple brackets and does not contact the fuel tank. The premixing section has multiple first cooling holes on its circumference. A cooling section is fixed at the end of the premixing section away from the fuel cartridge; The combustion section is fixed at one end of the cooling section, and the combustion section has multiple dilution holes around its circumference. An igniter is provided between the cooling section and the combustion section.

[0008] Furthermore, preferably, a venturi tube is coaxially arranged in the premixing section, and the throat of the venturi tube corresponds to the first cooling hole. The outer wall of the venturi tube near the fuel tank is fixed to the premixing section by a sealing ring, and the outer wall of the other end is fixed to the premixing section by multiple support blocks. A cooling channel is provided between the premixing section and the venturi tube.

[0009] Furthermore, preferably, a cone is coaxially fixed inside the end of the flame tube near the fuel tube, and multiple auxiliary gas injection heads extend into the cone, with swirl fans fixed to the outer walls of the multiple auxiliary gas injection heads.

[0010] Furthermore, preferably, the blades of adjacent swirl fans rotate in opposite directions.

[0011] Furthermore, preferably, the cone has a plurality of first outlets and second outlets circumferentially formed on its conical surface, and the plurality of first outlets and second outlets are alternately formed along the axial direction of the cone. The cone is sleeved on the outer wall of the main gas injection head, and a phase change ring is provided between the cone surface of the cone and the main gas injection head. The phase change ring is a shape memory metal. The outer wall of the main gas injection head has multiple mixing holes circumferentially opened at positions corresponding to the conical surface.

[0012] Further, preferably, the auxiliary gas injection head includes: The air injection tube has multiple sets of premixed inlets equidistantly opened along the axial direction on its outer wall. Each set of premixed inlets includes multiple premixed holes arranged along the circumference of the air injection tube. Multiple guide rings are configured and fixed at equal intervals to the inner wall of the gas injection pipe, and correspond one-to-one with the multiple sets of premixed inlets; The guide ring is closed at one end near the fuel cylinder, and the other end has an opening that is inclined toward the axis of the gas injection pipe.

[0013] Furthermore, preferably, the outer wall of the cooling section is fixed with multiple protrusions at equal intervals along the axial direction. Multiple second cooling holes are obliquely opened on the circumference of each protrusion. The inner wall of the cooling section is fixed with isolation rings at positions corresponding to the protrusions. One end of the isolation ring near the venturi tube is closed, and the other end is open. Multiple speed-increasing holes are opened on the closed surface of the isolation ring, which correspond to the cooling channel. The outer wall of the isolation ring is horizontally arranged with the inner wall of the cooling section, and the inner wall of the isolation ring is obliquely arranged to guide the mixed gas towards the axial direction of the cooling section.

[0014] Compared with the prior art, the present invention provides an air conditioning device for the combustion chamber of a hydrogen fuel cell gas turbine, which has the following advantages: In this invention, the segmented design of the flame tube allows for multiple diversions of compressed air, achieving multi-stage distribution and significantly reducing the risk of backfire. Furthermore, the compressed air entering through the dilution holes can be directly injected into the core of the high-temperature flame zone, rapidly reducing the combustion temperature and suppressing thermal NO₂. x The generation of the fuel and air, through the use of oppositely rotating blades in adjacent swirl fans, forms shear vortex disturbances, promoting the mixing of fuel and air. The alternating arrangement of the first and second outlets on the cone, together with the mixing holes, forms a dynamic airflow field, disrupting the formation of periodic vortices, effectively attenuating combustion oscillations, and ensuring the safe operation of the unit. Attached Figure Description

[0015] Figure 1 This is a cross-sectional schematic diagram of the overall structure of an air conditioning device for the combustion chamber of a hydrogen fuel cell gas turbine. Figure 2 A cross-sectional schematic diagram of the combustion chamber of a hydrogen fuel gas turbine combustion chamber air conditioning device; Figure 3 A schematic diagram of the regulating component structure of a combustion chamber air conditioning device for a hydrogen fuel cell gas turbine; Figure 4 This is a schematic diagram of the internal structure of the regulating component of a combustion chamber air conditioning device for a hydrogen fuel cell gas turbine. Figure 5 for Figure 4 A magnified structural diagram at point A; Figure 6 for Figure 4 A magnified structural diagram at point B; Figure 7 for Figure 4 A magnified structural diagram at point C; In the diagram: 1. Compressor chamber; 2. Combustion chamber; 3. Turbine chamber; 4. Airflow channel; 5. Adjustment assembly; 6. Injector; 7. Isolation ring 1; 51. Fuel tank; 52. Draft tube; 53. Flame tube; 54. Main injection head; 55. Auxiliary injection head; 56. Cone; 57. Swirl fan; 58. Venturi tube; 521. Air inlet; 531. Premixing section; 532. First cooling hole; 533. Cooling section; 534. 535 Combustion section; 541 Dilution hole; 551 Injection pipe; 552 Premixing hole; 553 Guide ring; 554 Guide surface; 561 First outlet; 562 Second outlet; 563 Phase change ring; 581 Sealing ring; 582 Support block; 583 Cooling channel; 5331 Protrusion block; 5332 Second cooling hole; 5333 Second isolation ring; 5334 Speed-increasing hole. Detailed Implementation

[0016] Reference Figures 1-7 The present invention provides a technical solution: a combustion chamber air conditioning device for a hydrogen fuel cell gas turbine, comprising: The air chamber 1 has an air inlet at one end; Combustion chamber 2 is fixed at the end of the compressor chamber 1 away from the air inlet; A turbine chamber 3 is fixed at one end of the combustion chamber 2 away from the compressor chamber 1, and a plurality of injection ports 6 are provided between the combustion chamber 2 and the turbine chamber 3; The combustion chamber 2 has an air flow channel 4 inside, and multiple adjusting components 5 are evenly fixed around the circumference of the air flow channel 4. One end of the adjusting component 5 extends into the injection port 6, and the adjusting component 5 and the injection port 6 are sealed by an isolation ring 7. The end of the adjusting component 5 away from the injection port 6 passes through the combustion chamber 2 and is fixed with a fuel cylinder 51. The fuel cylinder 51 is fixed at an angle to the combustion chamber 2, and the adjusting component 5 and the fuel cylinder 51 are arranged coaxially.

[0017] In this embodiment, the adjustment component 5 includes: The guide tube 52 is fixed on the combustion chamber 2 and located in the air flow channel 4. A conical tube is provided at one end away from the fuel cylinder 51. Multiple air inlets 521 are provided on the conical tube for receiving the compressed air from the compressor chamber 1. The flame tube 53 is coaxially fixed inside the guide tube 52; The main gas injection head 54 is fixed at the axial position of the fuel cylinder 51, and one end extends into the flame cylinder 53; Multiple auxiliary gas injection heads 55 are configured and evenly distributed around the main gas injection head 54 and fixed to the fuel cylinder 51. One end of the auxiliary gas injection head 55 extends into the flame cylinder 53.

[0018] It should be noted that the axial direction of the air inlet 521 is perpendicular to the conical surface of the conical cylinder. In other words, after the air is compressed through the compressor chamber 1, it first enters the air flow channel 4, and then enters the guide tube 52 through the multiple air inlets 521 of the conical tube. At this time, the design of the conical tube can avoid a significant reduction in the flow velocity of the compressed air. The compressed air first flows along the outer wall of the conical surface of the conical tube, and then enters through the air inlet 521. When entering, the perpendicular arrangement of the air inlet 521 and the conical surface can cause the compressed air to turn, thereby flowing towards the fuel tank 51, avoiding excessive loss of flow velocity.

[0019] In a preferred embodiment, the flame tube 53 includes: The premixing section 531 is coaxially fixed inside the guide tube 52 by multiple brackets and does not contact the fuel tank 51. The premixing section 531 has multiple first cooling holes 532 on its circumference. Cooling section 533 is fixed at one end of premix section 531 away from fuel tank 51; Combustion section 534 is fixed at one end of cooling section 533, and multiple dilution holes 535 are provided around the circumference of combustion section 534. An igniter is provided between cooling section 533 and combustion section 534.

[0020] It should be explained that the main channel for compressed air to enter the flame tube 53 is between the premixing section 531 and the fuel tube 51. When it flows through the combustion section 534, it undergoes a preliminary diversion through the dilution hole 535. When it flows through the cooling section 533, it undergoes a secondary diversion. When it flows through the premixing section 531, it undergoes a tertiary diversion through the first cooling hole 532. Finally, most of the remaining compressed air enters the flame tube 53 through the top of the premixing section 531, thus completing the initial adjustment of the compressed air flow direction.

[0021] It is worth mentioning that the compressed air entering through the dilution hole 535 can be directly injected into the core of the high-temperature zone of the flame, rapidly reducing the combustion temperature and suppressing thermal NO. x The generation of .

[0022] Preferably, a venturi tube 58 is coaxially arranged inside the premixing section 531, and the throat of the venturi tube 58 corresponds to the first cooling hole 532. The outer wall of the venturi tube 58 near the fuel tank 51 is fixed to the premixing section 531 by a sealing ring 581, and the outer wall of the other end is fixed to the premixing section 531 by multiple support blocks 582. A cooling channel 583 is provided between the premixing section 531 and the venturi tube 58.

[0023] In other words, when the compressed air is split into two streams, the compressed air can directly cool the outer wall of the venturi tube 58 and flow through the cooling channel 583, thereby forming an auxiliary air film on the inner wall of the cooling section 533.

[0024] In addition, the compressed air first enters the throat of the Venturi tube 58. The space between this location and the cooling channel 583 between the premixing section 531 is relatively large. Then, the compressed air flows towards the unclosed support block 582. At this time, the space of the cooling channel 583 decreases, thereby increasing the flow rate of the compressed air. In other words, the Venturi effect (a physical phenomenon in which the flow rate of a fluid increases while the static pressure decreases when it passes through a constricted pipe) is formed on the outer wall of the Venturi tube 58. Thus, the Venturi effect is formed both inside and outside the Venturi tube 58, which not only increases the mixing effect of the fuel inside the Venturi tube 58, but also increases the flow rate of the compressed air on the outer wall of the Venturi tube 58, thereby forming an auxiliary air film and reducing the possibility of backfire.

[0025] Preferably, a cone 56 is coaxially fixed inside the end of the flame tube 53 near the fuel tube 51, and a plurality of auxiliary gas injection heads 55 extend into the cone 56, and a swirl fan 57 is fixed to the outer wall of the plurality of auxiliary gas injection heads 55.

[0026] Preferably, the blades of adjacent swirl fans 57 rotate in opposite directions.

[0027] In other words, when compressed air passes through the swirl fan 57, it will rotate, and adjacent swirl fans 57 use blades with opposite rotation directions, which can form shear vortex disturbances and promote the mixing of fuel and compressed air.

[0028] Preferably, the cone 56 has a plurality of first outlets 561 and second outlets 562 circumferentially formed on the cone surface, and the plurality of first outlets 561 and second outlets 562 are alternately formed along the axial direction of the cone 56. It should be noted that the mixed gas discharged from the first outlet 561 has a first swirl, and the mixed gas discharged from the second outlet 562 has a second swirl. The first and second swirls are in opposite directions, thereby performing secondary shearing, further improving the mixing effect and enhancing the stability of combustion. The cone 56 is sleeved on the outer wall of the main gas injection head 54, and a phase change ring 563 is provided between the cone surface of the cone 56 and the main gas injection head 54. The phase change ring 563 is a shape memory metal. Additionally, it should be explained that phase change ring 563 is a material that achieves physical contraction and expansion through temperature changes; specifically, it is a shape memory metal. Preferably, the phase change ring 563 set between the cone 56 and the main injection head 54 can automatically adjust the gap between the cone 56 and the main injection head 54 according to temperature changes. When the temperature is high, it expands to close the gap and reduce the discharge of the mixture. When the temperature is low, it contracts to expand the gap and increase the discharge of the mixture, thereby achieving dynamic matching of combustion conditions and widening the stable operating range. The outer wall of the main air injection head 54 is provided with multiple mixing holes 541 at the corresponding positions of the conical surface.

[0029] The mixing orifice 541 allows the pre-mixed gas to enter the main injection head 54 in advance and mix with the hydrogen fuel inside the main injection head 54, thereby increasing the proportion of hydrogen fuel in the mixed gas, optimizing the air-fuel ratio, and reducing NO. x The generation of.

[0030] In a preferred embodiment, the auxiliary gas injection head 55 includes: The air injection pipe 551 has multiple sets of premixed inlets equidistantly provided on its outer wall along the axial direction. Each set of premixed inlets includes multiple premixed holes 552 arranged along the circumference of the air injection pipe 551. Multiple guide rings 553 are configured and fixed at equal intervals to the inner wall of the gas injection pipe 551, and correspond one-to-one with multiple sets of premixed inlets; The guide ring 553 is closed at one end near the fuel cylinder 51, and the other end has an opening inclined towards the axis of the gas injection pipe 551 using a guide surface 554.

[0031] In other words, when compressed air enters through the premixing hole 552, it is guided by the guide ring 553 to flow axially toward the injection pipe 551, thereby initially mixing with the incoming hydrogen fuel and improving the mixing efficiency.

[0032] In a preferred embodiment, the outer wall of the cooling section 533 is fixed with a plurality of protrusions 5331 at equal intervals along the axial direction. The protrusions 5331 are provided with a plurality of second cooling holes 5332 circumferentially inclined. The inner wall of the cooling section 533 is fixed with a second isolation ring 5333 at a position corresponding to the protrusions 5331. The second isolation ring 5333 is closed at one end near the venturi tube 58 and has an opening at the other end. The closed surface of the second isolation ring 5333 is provided with a plurality of speed-increasing holes 5334. The plurality of speed-increasing holes 5334 correspond to the cooling channel 583. The outer wall of the second isolation ring 5333 is horizontally arranged with the inner wall of the cooling section 533, and the inner wall of the second isolation ring 5333 is inclined to guide the mixed gas to the axial direction of the cooling section 533.

[0033] The horizontal arrangement of the outer wall of the second isolation ring 5333 and the inner wall of the cooling section 533 creates a stable direct current gas film on the outer wall of the cooling section 533. The direct current gas film can pass through the previous second isolation ring 5333 through the speed-increasing hole 5334, thus forming a continuous gas film. This improves the cooling effect and suppresses backfire. The inclined arrangement of the inner wall of the second isolation ring 5333 allows the mixed gas to concentrate in the axial direction, making the flame formation more concentrated and reducing the backfire phenomenon caused by the flame spreading to the inner wall of the flame tube 53.

[0034] In addition, the auxiliary air film flowing out from the cooling channel 583 can be connected to the air film through the speed-increasing hole 5334, thereby forming an uninterrupted air film and improving the protection and cooling effect.

[0035] In practice, air first enters the compressor chamber 1 for compression. The compressed air then enters the airflow channel 4 and passes through the air inlet 521 of the guide tube 52 into the flame tube 53. It then flows sequentially through the combustion section 534, the cold zone section 533, and the premixing section 531 for splitting. The split compressed air then enters the cone 56 through one end of the premixing section 531 and is rotated by the swirl fan 57. It is split again when passing through the auxiliary injection head 55. At this point, hydrogen fuel is injected through the main injection head 54 and the auxiliary injection head 55. The compressed air is initially mixed in the auxiliary injection head 55, and then mixed a second time in the cone 56. After that, it is mixed a third time through the first outlet 561 and the second outlet 562 of the cone. At the same time, part of the second-mixed gas enters the main injection head 54 to increase its concentration, forming a high-concentration mixture. Then, the high-concentration mixture and the third-mixed gas are accelerated and finally mixed through the venturi tube 58, and ignited after the cooling section 533. The high-temperature gas is injected into the turbine chamber 3 through the injection port 6 for driving.

[0036] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An air conditioning device for the combustion chamber of a hydrogen fuel cell gas turbine, characterized in that, include: A compressor chamber (1) has an air inlet at one end; a combustion chamber (2) is fixed at the end of the compressor chamber (1) away from the air inlet; a turbine chamber (3) is fixed at the end of the combustion chamber (2) away from the compressor chamber (1), and multiple injection ports (6) are provided between the combustion chamber (2) and the turbine chamber (3); wherein, an air flow channel (4) is provided inside the combustion chamber (2), and multiple adjustment components (5) are uniformly fixed around the circumference of the air flow channel (4), one end of the adjustment component (5) extends into the injection port (6), and the adjustment component (5) and the injection port (6) are sealed by an isolation ring (7), the end of the adjustment component (5) away from the injection port (6) passes through the combustion chamber (2) and is fixed with a fuel cylinder (51), and the fuel cylinder (51) is fixed at an inclination to the combustion chamber (2), and the adjustment component (5) and the fuel cylinder (51) are coaxially arranged; The adjustment component (5) includes: The air guide tube (52) is fixed on the combustion chamber (2) and located in the air flow channel (4); The flame tube (53) is coaxially fixed inside the guide tube (52); The main gas injection head (54) is fixed at the axial position of the fuel cylinder (51), and one end extends into the flame cylinder (53); Auxiliary gas injection heads (55) are configured in multiples and are evenly distributed around the main gas injection head (54) and fixed to the fuel cylinder (51). One end of the auxiliary gas injection head (55) extends into the flame cylinder (53). The flame tube (53) includes a premixing section (531), a cooling section (533), and a combustion section (534). The premixing section (531) has a plurality of first cooling holes (532) circumferentially formed. A venturi tube (58) is coaxially arranged inside the premixing section (531), and the throat of the venturi tube (58) corresponds to the first cooling hole (532). A cooling channel (583) is provided between the premixing section (531) and the venturi tube (58). A cone (56) is coaxially fixed inside one end of the flame tube (53) near the fuel tube (51), and multiple auxiliary gas injection heads (55) extend into the cone (56). The cone (56) is sleeved on the outer wall of the main gas injection head (54), and a phase change ring (563) is provided between the cone surface of the cone (56) and the main gas injection head (54), and the phase change ring (563) is a shape memory metal; The outer wall of the cooling section (533) is fixed with a plurality of protrusions (5331) at equal intervals along the axial direction. The protrusions (5331) are provided with a plurality of second cooling holes (5332) at an inclined circumference. The inner wall of the cooling section (533) is fixed with a second isolation ring (5333) at a position corresponding to the protrusions (5331). The second isolation ring (5333) is closed at one end near the venturi tube (58) and open at the other end. The closed surface of the second isolation ring (5333) is provided with a plurality of speed-increasing holes (5334), which correspond to the cooling channel (583).

2. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The guide tube (52) has a conical tube at one end away from the fuel cylinder (51), and the conical tube has multiple air inlets (521) for receiving the compressed air from the compressor chamber (1).

3. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The premixing section (531) is coaxially fixed inside the guide tube (52) by multiple brackets and does not contact the fuel tank (51); The cooling section (533) is fixed at one end of the premixing section (531) away from the fuel cylinder (51); The combustion section (534) is fixed at one end of the cooling section (533), and the combustion section (534) has a plurality of dilution holes (535) around its circumference. An igniter is provided between the cooling section (533) and the combustion section (534).

4. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The outer wall of the venturi tube (58) near the fuel cylinder (51) is fixed to the premix section (531) by a sealing ring (581), and the outer wall of the other end is fixed to the premix section (531) by multiple support blocks (582).

5. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The outer walls of the multiple auxiliary gas injection heads (55) are all fixed with swirl fans (57).

6. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 5, characterized in that, The blades of the adjacent swirl fans (57) rotate in opposite directions.

7. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The cone (56) has a plurality of first outlets (561) and second outlets (562) circumferentially opened on the cone surface, and the plurality of first outlets (561) and second outlets (562) are alternately opened along the axial direction of the cone (56). The outer wall of the main air injection head (54) has a plurality of mixing holes (541) circumferentially opened at the position corresponding to the cone surface.

8. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The auxiliary gas injection head (55) includes: The air injection pipe (551) has multiple sets of premixed inlets equidistantly opened along the axial direction on its outer wall. Each set of premixed inlets includes multiple premixed holes (552) arranged along the circumference of the air injection pipe (551). Multiple guide rings (553) are configured and fixed at equal intervals to the inner wall of the gas injection pipe (551), and correspond one-to-one with multiple sets of premixed inlets; The guide ring (553) is closed at one end near the fuel cylinder (51), and the other end has an opening inclined toward the axis of the gas injection pipe (551) using a guide surface (554).

9. The combustion chamber air conditioning device for a hydrogen fuel cell gas turbine according to claim 1, characterized in that, The outer wall of the second isolation ring (5333) is horizontally arranged with the inner wall of the cooling section (533), and the inner wall of the second isolation ring (5333) is inclined to guide the mixed gas to the axial direction of the cooling section (533).

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