A low NOx hydrogen combustion chamber and gas turbine

Abstract

The present invention provides a low NOx hydrogen combustion chamber and a gas turbine, wherein the combustion chamber comprises: an outer ring of the combustion chamber and an inner ring of the combustion chamber, wherein the inner ring of the combustion chamber is coaxially sleeved in the inner cavity of the outer ring of the combustion chamber, and a main flow channel annular cavity for rotating detonation combustion is formed between the annular wall of the outer ring of the combustion chamber and the annular wall of the inner ring of the combustion chamber; the main flow channel annular cavity comprises a front section cavity, a middle section cavity and a rear section cavity in the direction of gas flow, an injection ring is arranged circumferentially in the front section cavity, a hydrogen annular cavity for collecting hydrogen is arranged in the inner cavity of the injection ring, and a plurality of hydrogen nozzles are arranged circumferentially on the nozzle side of the injection ring, for ejecting hydrogen fuel in the hydrogen annular cavity from the hydrogen nozzle; an air main inlet is arranged upstream of the main flow channel annular cavity for introducing air, so that air and hydrogen fuel are mixed and ignited in the middle section cavity for rotating detonation combustion. The present invention can achieve the purpose of reducing the emission of harmful substances NOx and carbon emissions and improving combustion efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a low NOx hydrogen combustion chamber and a gas turbine. Background Art

[0002] The combustion chamber of a gas turbine is a component that mixes fuel and air and burns them in it to produce high-temperature and high-pressure gas to drive the rotating parts. The design and performance of the combustion chamber have an important impact on the efficiency, power output and emission level of the gas turbine. The combustion chamber of a gas turbine is usually composed of a combustion chamber body, a burner, a fuel nozzle, a combustion air supply pipeline, an igniter and other components. The combustion chamber body is a closed container with a burner and a fuel nozzle inside. The burner is a component that mixes fuel and air and ignites it. There are many structures and forms, such as disc type, ring type, spray type, etc. The fuel nozzle is a component that sprays fuel into the burner. Its parameters such as quantity, position and layout will also affect the performance of the combustion chamber.

[0003] During the operation of a gas turbine, fuel and air are mixed and ignited through the fuel nozzle and burner to produce high-temperature and high-pressure gas. The gas expands and accelerates in the combustion chamber, and then is converted into kinetic energy through the rotating components to drive the generator or other equipment. At the same time, the design of the gas turbine combustion chamber also needs to take into account the issues of reducing emissions and improving combustion efficiency.

[0004] At present, the main fuel for gas turbines is fossil fuels such as kerosene and natural gas, and the combustion of these fuels will produce a large amount of carbon emissions. As the demand for zero-carbon power generation in the future increases, many gas turbine manufacturers are exploring hydrogen fuel combustion chamber technology. However, the main disadvantage of using hydrogen as fuel for traditional gas turbines is that the high combustion temperature and rapid flame propagation speed of hydrogen will cause a significant increase in nitrogen oxide (NOx) emissions. This is because the combustion rate of hydrogen is faster than that of traditional fuels, and it is easy to form a high-temperature and high-pressure combustion area in the combustion chamber, which in turn leads to increased NOx emissions. In addition, the design and control system of traditional gas turbines are generally not suitable for hydrogen fuel, and the combustion chamber and control system need to be improved and adjusted, which increases the cost and technical difficulty. Summary of the invention

[0005] In view of this, the embodiments of the present application provide a low NOx hydrogen combustion chamber and a gas turbine to reduce the emission of harmful substances NOx and carbon emissions and improve combustion efficiency.

[0006] The embodiment of the present application provides the following technical solution: a low NOx hydrogen combustion chamber, comprising:

[0007] An outer ring of a combustion chamber and an inner ring of a combustion chamber, wherein the inner ring of the combustion chamber is coaxially sleeved in the inner cavity of the outer ring of the combustion chamber, and a main flow channel annular cavity for rotating detonation combustion is formed between the annular wall of the outer ring of the combustion chamber and the annular wall of the inner ring of the combustion chamber;

[0008] The main flow channel annular cavity includes a front section cavity, a middle section cavity and a rear section cavity in sequence in the direction of gas flow, an injection ring is circumferentially arranged in the front section cavity, a hydrogen annular cavity for collecting hydrogen is arranged in the inner cavity of the injection ring, and a plurality of hydrogen nozzles are circumferentially arranged on the nozzle side of the injection ring for spraying the hydrogen fuel in the hydrogen annular cavity from the hydrogen nozzles; an air main inlet is arranged upstream of the main flow channel annular cavity for introducing air, so that the air and hydrogen fuel are mixed and ignited in the middle section cavity and then undergo rotational detonation combustion.

[0009] According to one embodiment of the present application, an outer ring hydrogen-cooled shell is arranged in a closed manner on the outer wall of the combustion chamber ring corresponding to the middle section cavity, and an outer ring cooling channel is formed between the outer ring hydrogen-cooled shell and the ring wall of the combustion chamber ring. Liquid hydrogen is introduced into the outer ring cooling channel to cool the main channel ring cavity.

[0010] According to one embodiment of the present application, a plurality of outer ring radial holes are arranged on the ring wall of the outer ring of the combustion chamber corresponding to the outer ring cooling channel, so that the liquid hydrogen in the outer ring cooling channel enters the middle section cavity through the outer ring radial holes, and forms a cooling air film on the inner wall surface of the outer ring of the combustion chamber in the middle section cavity.

[0011] According to one embodiment of the present application, an inner ring hydrogen-cooled shell is arranged in a closed manner on the inner wall of the inner ring of the combustion chamber corresponding to the middle section cavity, and an inner ring cooling channel is formed between the inner ring hydrogen-cooled shell and the ring wall of the inner ring of the combustion chamber, and liquid hydrogen is introduced into the inner ring cooling channel to cool the main channel ring cavity.

[0012] According to one embodiment of the present application, a plurality of inner ring radial holes are arranged on the ring wall of the inner ring of the combustion chamber corresponding to the inner ring cooling channel, so that the liquid hydrogen in the inner ring cooling channel enters the middle section cavity through the inner ring radial holes, and forms a cooling air film on the outer wall surface of the combustion chamber ring in the middle section cavity.

[0013] According to one embodiment of the present application, supplementary combustion air inlets are respectively provided on the combustion chamber outer ring and the combustion chamber inner ring corresponding to the rear section cavity, for introducing air and continuing mixed combustion in the rear section cavity to burn out the remaining hydrogen after the rotating detonation combustion in the middle section cavity.

[0014] According to one embodiment of the present application, a mixing cooling air inlet is also provided on the outer ring of the combustion chamber corresponding to the rear section cavity. In the direction of gas flow, the mixing cooling air inlet is located behind the supplementary combustion air inlet, and is used to introduce air so that the air is mixed with the smoke generated by the combustion and then discharged from the main channel ring cavity.

[0015] According to an embodiment of the present application, the number of the mixing cooling air inlet and the number of the supplementary combustion air inlet are both multiple, and are evenly distributed circumferentially in the rear section cavity.

[0016] According to one embodiment of the present application, throats are formed between the injection ring and the combustion chamber outer ring and the combustion chamber inner ring on both sides, so that the air entering from the main air inlet enters the main channel ring cavity after being throttled by the throat.

[0017] An embodiment of the present invention further provides a gas turbine, comprising a compressor, a low NOx hydrogen combustion chamber as claimed in any one of claims 1 to 9, and a turbine;

[0018] The compressor is coaxially connected to the turbine, air is introduced into the air inlet of the compressor, the air outlet of the compressor is connected to the low NOx hydrogen combustion chamber, and the flue gas outlet of the low NOx hydrogen combustion chamber is connected to the turbine, so that the flue gas generated by combustion drives the turbine to do work.

[0019] Compared with the prior art, at least one of the above-mentioned technical solutions adopted in the embodiments of this specification can achieve the following beneficial effects: the combustion chamber of the embodiment of the present invention adopts hydrogen fuel combustion, which reduces carbon emissions. In terms of combustion chamber structural design, by adopting detonation combustion technology, it can ensure that hydrogen fuel burns quickly in the gas turbine combustion chamber, reduce the generation of thermal NOx, and improve combustion efficiency, thereby reducing the emission of nitrogen oxides of the hydrogen fuel gas turbine to meet the emission indicators, and reduce the equipment investment cost and subsequent maintenance cost of the hydrogen fuel gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 is a schematic structural diagram of an embodiment of the present invention;

[0022] In the figure, 1-main air inlet, 2-hydrogen fuel inlet, 3-hydrogen annular cavity, 4-hydrogen nozzle, 5-outer ring gas hydrogen outlet, 6-outer ring liquid hydrogen inlet, 7-supplementary combustion air inlet, 8-mixing cooling air inlet, 9-inner ring liquid hydrogen inlet, 10-inner ring gas hydrogen outlet, 11-inner ring cooling air film, 12-outer ring cooling air film, 13-radial hole, 14-inner ring front section, 15-inner ring middle section, 16-inner ring hydrogen cooling shell, 17-inner ring cooling channel, 18-inner ring rear section, 19-injection ring, 20-outer ring front section, 21-throat, 22-outer ring middle section, 23-outer ring hydrogen cooling shell, 24-outer ring cooling channel, 25-outer ring rear section. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0024] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0025] like Figure 1 As shown, an embodiment of the present invention provides a low NOx hydrogen combustion chamber, comprising: a combustion chamber outer ring and a combustion chamber inner ring, the combustion chamber inner ring being coaxially sleeved in the inner cavity of the combustion chamber outer ring, a main flow channel annular cavity for rotating detonation combustion is formed between the annular wall of the combustion chamber outer ring and the annular wall of the combustion chamber inner ring; the main flow channel annular cavity comprises a front section cavity, a middle section cavity and a rear section cavity in the direction of gas flow, the front section cavity comprises an outer ring front section 20 and an inner ring front section 14, the middle section cavity comprises an outer ring middle section 22 and an inner ring middle section 15, and the rear section cavity comprises an outer ring rear section 25 and an inner ring rear section 18. An injection ring 19 is circumferentially arranged in the front section cavity, and a hydrogen ring cavity 3 for collecting hydrogen is arranged in the inner cavity of the injection ring 19. A plurality of hydrogen nozzles 4 are circumferentially arranged on the nozzle side of the injection ring 19 for spraying the hydrogen fuel in the hydrogen ring cavity 3 out of the hydrogen nozzles 4; an air main inlet 1 is arranged upstream of the main flow channel ring cavity for introducing air so that the air and hydrogen fuel are mixed and ignited in the middle section cavity to perform rotational detonation combustion.

[0026] Rotating detonation combustion is a combustion technology that achieves combustion through a rotating detonation wave. A detonation wave is a shock wave that propagates in a detonation reaction, allowing the reactants and oxygen to react quickly after contact. Rotating detonation combustion is a relatively new technology that is currently used in the automotive, aviation and aerospace industries, mainly to improve combustion efficiency and reduce pollution.

[0027] The hydrogen combustion chamber of the embodiment of the present invention uses hydrogen as fuel for combustion, which overcomes the defect that the traditional gas turbine uses fossil fuels such as kerosene and natural gas as the main fuel, resulting in a large amount of carbon emissions during the combustion process, and achieves the purpose of zero carbon emissions. In order to achieve a hydrogen combustion process with low NOx generation, the embodiment of the present invention adopts a rotating detonation combustion chamber structure to reduce the generation of thermal NOx during the combustion process. The generation of thermal NOx is a slow reaction process, which is formed by the reaction of N2 in the combustion air with reactants such as O and OH and molecular O2. Therefore, the characteristic of rapid detonation after ignition of the rotating detonation combustion chamber is utilized to increase the reaction speed and reduce the generation of thermal NOx. In addition, since the hydrogen injection during rotating detonation combustion is excessive, the combustion equivalence ratio is greater than 1, and there is excess hydrogen after combustion, the generation of NOx can be further suppressed, thereby achieving the purpose of reducing the emission of harmful substances NOx and carbon emissions and improving combustion efficiency.

[0028] On the other hand, in this embodiment, an injection ring 19 is arranged in the front cavity of the combustion chamber, and hydrogen fuel is added into the combustion chamber by injection. The fuel and air can be better mixed to form premixed air, which is beneficial to the stability of the downstream continuous rotating detonation.

[0029] Since the combustion temperature of rotating detonation combustion is very high, it is necessary to solve the cooling problem of detonation combustion so as to keep the temperature of the combustion engine within a suitable range. In one embodiment of the present invention, an outer ring hydrogen-cooled shell 23 is provided on the outer wall of the outer ring of the combustion chamber corresponding to the middle section cavity in a closed manner, and an outer ring cooling channel 24 is formed between the outer ring hydrogen-cooled shell 23 and the outer ring wall of the combustion chamber, and liquid hydrogen is introduced into the outer ring cooling channel 24 to cool the main channel ring cavity.

[0030] In the specific structure, the outer ring hydrogen cooling shell 23 is provided with an outer ring liquid hydrogen inlet 6 and an outer ring gas hydrogen outlet 5 respectively; liquid hydrogen is introduced into the outer ring cooling channel 24 through the outer ring liquid hydrogen inlet 6 to cool the main channel ring cavity. After cooling, the liquid hydrogen absorbs heat and gasifies to become gas hydrogen, which is discharged from the outer ring gas hydrogen outlet 5. The gas hydrogen discharged from the outer ring gas hydrogen outlet 5 can be introduced into the hydrogen ring cavity 3 of the injection ring 19 through the hydrogen fuel inlet 2 provided on the outer ring of the combustion chamber, and used for the rotary detonation combustion in the main channel ring cavity. While the hydrogen fuel is used as a coolant, it is used for combustion after recovering heat, which reduces the combustion power and improves the combustion efficiency.

[0031] In a further preferred embodiment of the present invention, a plurality of radial holes 13 of the outer ring are arranged on the ring wall of the outer ring of the combustion chamber corresponding to the outer ring cooling channel 24, so that the liquid hydrogen in the outer ring cooling channel 24 enters the middle section cavity through the radial holes 13, and forms an outer ring cooling air film 12 on the inner wall surface of the outer ring of the combustion chamber in the middle section cavity. Part of the liquid hydrogen in the outer ring cooling channel 24 enters the middle section cavity through the radial holes 13, and forms a cooling air film on the inner wall surface of the outer ring of the combustion chamber, which can further play a role in cooling and heat insulation, and the cooling air film on the inner wall of the chamber can moderately reduce the combustion temperature, overcome the defect of high combustion temperature of hydrogen fuel, and can also effectively reduce the generation of thermal NOx during combustion, so as to achieve the purpose of reducing the emission of harmful substances NOx.

[0032] In an embodiment of the present invention, an inner ring hydrogen-cooled shell 16 is provided on the inner wall of the inner ring of the combustion chamber corresponding to the middle cavity in a closed manner, and an inner ring cooling channel 17 is formed between the inner ring hydrogen-cooled shell 16 and the ring wall of the inner ring of the combustion chamber, and liquid hydrogen is introduced into the inner ring cooling channel 17 to cool the main channel ring cavity. In the specific structure, the inner ring hydrogen-cooled shell 16 is provided with an inner ring liquid hydrogen inlet 9 and an inner ring gas hydrogen outlet 10 respectively; liquid hydrogen is introduced into the inner ring cooling channel 17 through the inner ring liquid hydrogen inlet 9 to cool the main channel ring cavity, and after cooling, the liquid hydrogen absorbs heat and gasifies to become gas hydrogen, which is discharged from the inner ring gas hydrogen outlet 10. The gas hydrogen discharged from the inner ring gas hydrogen outlet 10 can be introduced into the hydrogen ring cavity 3 of the injection ring 19 through the hydrogen fuel inlet 2 provided on the outer ring of the combustion chamber, and is used for the rotary detonation combustion in the main channel ring cavity. While the hydrogen fuel is used as a coolant, the heat is recovered and used for combustion, which reduces the combustion power and improves the combustion efficiency.

[0033] In this embodiment, an inner ring cooling channel 17 is further provided on the basis of the outer ring cooling channel 24, and the inner and outer rings of the main channel ring cavity are cooled simultaneously, which greatly improves the cooling effect and ensures the stable working performance of the detonation combustion chamber. In a further preferred embodiment of this embodiment, a plurality of inner ring radial holes 13 are provided on the ring wall of the inner ring of the combustion chamber corresponding to the inner ring cooling channel 17, so that part of the liquid hydrogen in the inner ring cooling channel 17 enters the middle section cavity through the radial holes 13, and forms an inner ring cooling air film 11 on the outer wall surface of the inner ring of the combustion chamber in the middle section cavity. A cooling air film is formed on both the inner and outer wall surfaces of the middle section cavity, which improves the cooling effect and effectively reduces the combustion temperature of hydrogen fuel, thereby achieving low NOx emissions.

[0034] In the embodiment of the present invention, the radial holes 13 can be formed by processing metal materials, or made of porous materials. The porous materials can be existing high temperature resistant porous metals, porous ceramics, etc.

[0035] In an embodiment of the present invention, a supplementary combustion air inlet 7 is respectively provided on the combustion chamber outer ring and the combustion chamber inner ring corresponding to the rear section cavity, for introducing air and continuing mixed combustion in the rear section cavity to burn out the remaining hydrogen after the rotating detonation combustion in the middle section cavity.

[0036] In the middle section of the main channel annular cavity, the combustion temperature of the rotating detonation combustion is greater than 2300K, and excessive hydrogen is injected through the hydrogen nozzle 4, and the combustion equivalence ratio is greater than 1. At this time, since the hydrogen is excessive, there is some residual hydrogen at the outlet of the middle section cavity, and it is necessary to perform supplementary combustion in the rear section cavity to burn the hydrogen completely. Therefore, in this embodiment, supplementary combustion air is introduced into the rear section cavity, and the supplementary combustion air and the unburned hydrogen in the middle section cavity are further burned to improve the combustion efficiency.

[0037] In an embodiment of the present invention, a mixing cooling air inlet 8 is also provided on the outer ring of the combustion chamber corresponding to the rear section cavity. In the direction of gas flow, the mixing cooling air inlet 8 is located behind the supplementary combustion air inlet 7, and is used to introduce air, so that the air is mixed with the flue gas generated by the combustion and then discharged from the main channel annular cavity. Air is introduced through the above-mentioned mixing cooling air inlet 8. The mixing is mainly to reduce the combustion chamber outlet temperature. After the hydrogen in the middle section cavity undergoes continuous rotational detonation combustion, further supplementary combustion is added. The outlet temperature of the main channel annular cavity of the combustion chamber is still very high, generally above 2000K. The turbine cannot work at this high temperature. Direct discharge of the combustion flue gas will affect the turbine performance. Therefore, air is introduced to cool the high-temperature flue gas. After the mixing air is mixed, the outlet temperature of the combustion chamber is reduced. The flue gas temperature is reduced to below 1200-1700K before entering the turbine to ensure the normal operation of the turbine.

[0038] In the above embodiment, the number of the mixed cooling air inlet 8 and the supplementary combustion air inlet 7 are both multiple and are evenly distributed circumferentially in the rear section cavity to ensure the uniformity of the introduced air.

[0039] In the embodiment of the present invention, the injection ring 19 and the combustion chamber outer ring and the combustion chamber inner ring on both sides respectively form throats 21, so that the air entering from the main air inlet 1 enters the main flow channel annular cavity after being throttled by the throat 21. The throat 21 is formed by the channel contraction structure formed between the injection ring 19 and the combustion chamber outer ring and the combustion chamber inner ring on both sides. The structure of the throat 21 allows the air to enter the main flow channel annular cavity uniformly, and after the air is throttled at the throat 21, supersonic flow is achieved, so that the detonation wave generated during the downstream rotating detonation combustion will not be transmitted back to the upstream compressor, thereby ensuring the normal operation of the compressor.

[0040] An embodiment of the present invention also provides a gas turbine, comprising a compressor, a low NOx hydrogen combustion chamber as described above, and a turbine; the compressor is coaxially connected to the turbine, air is introduced into an air inlet of the compressor, an air outlet of the compressor is connected to the low NOx hydrogen combustion chamber, and a flue gas outlet of the low NOx hydrogen combustion chamber is connected to the turbine, so that the flue gas generated by combustion drives the turbine to do work.

[0041] During the operation of the gas turbine, the hydrogen fuel and air in the low NOx hydrogen combustion chamber are mixed through the fuel nozzle and burner and ignited to produce high-temperature and high-pressure combustion gas. The combustion gas expands and accelerates in the combustion chamber, and then is converted into kinetic energy through the rotating components to drive the generator or other equipment.

[0042] The low NOx hydrogen combustion chamber of the embodiment of the present invention and the gas turbine including the combustion chamber use liquid hydrogen as fuel, reduce carbon emissions, and improve combustion efficiency. The three-stage design of the combustion chamber can ensure that the hydrogen fuel is fully burned in the gas turbine combustion chamber and can significantly reduce the generation of nitrogen oxides, thereby reducing the emission of nitrogen oxides of the hydrogen fuel gas turbine to meet emission indicators and reduce the equipment investment cost and subsequent maintenance cost of the hydrogen fuel gas turbine.

[0043] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A low NOx hydrogen combustion chamber, characterized in that: include: An outer ring of a combustion chamber and an inner ring of a combustion chamber, wherein the inner ring of the combustion chamber is coaxially sleeved in the inner cavity of the outer ring of the combustion chamber, and a main flow channel annular cavity for rotating detonation combustion is formed between the annular wall of the outer ring of the combustion chamber and the annular wall of the inner ring of the combustion chamber; The main flow channel annular cavity includes a front section cavity, a middle section cavity and a rear section cavity in sequence in the direction of gas flow, an injection ring is circumferentially arranged in the front section cavity, a hydrogen annular cavity for collecting hydrogen is arranged in the inner cavity of the injection ring, and a plurality of hydrogen nozzles are circumferentially arranged on the nozzle side of the injection ring for spraying the hydrogen fuel in the hydrogen annular cavity from the hydrogen nozzles; an air main inlet is arranged upstream of the main flow channel annular cavity for introducing air, so that the air and hydrogen fuel are mixed and ignited in the middle section cavity to perform rotating detonation combustion; An outer ring hydrogen-cooled shell is provided in a closed manner on the outer ring outer wall of the combustion chamber corresponding to the middle section cavity, and an outer ring cooling channel is formed between the outer ring hydrogen-cooled shell and the outer ring wall of the combustion chamber. Liquid hydrogen is introduced into the outer ring cooling channel to cool the main channel ring cavity; A plurality of outer ring radial holes are arranged on the ring wall of the outer ring of the combustion chamber corresponding to the outer ring cooling channel, so that the liquid hydrogen in the outer ring cooling channel enters the middle section cavity through the outer ring radial holes, and forms a cooling gas film on the inner wall surface of the outer ring of the combustion chamber in the middle section cavity; An inner ring hydrogen-cooled shell is provided in a closed manner on the inner wall of the inner ring of the combustion chamber corresponding to the middle section cavity, and an inner ring cooling channel is formed between the inner ring hydrogen-cooled shell and the ring wall of the inner ring of the combustion chamber, and liquid hydrogen is introduced into the inner ring cooling channel to cool the main channel ring cavity; A plurality of inner ring radial holes are arranged on the ring wall of the inner ring of the combustion chamber corresponding to the inner ring cooling channel, so that the liquid hydrogen in the inner ring cooling channel enters the middle section cavity through the inner ring radial holes, and forms a cooling gas film on the outer wall surface of the inner ring of the combustion chamber in the middle section cavity; The combustion chamber outer ring and the combustion chamber inner ring corresponding to the rear chamber are respectively provided with supplementary combustion air inlets for introducing air to continue mixed combustion in the rear chamber, so as to burn out the remaining hydrogen after the rotating detonation combustion in the middle chamber; A mixing cooling air inlet is also provided on the outer ring of the combustion chamber corresponding to the rear section cavity. In the direction of gas flow, the mixing cooling air inlet is located behind the supplementary combustion air inlet and is used to introduce air so that the air is mixed with the smoke generated by combustion and then discharged from the main channel ring cavity.

2. The low NOx hydrogen combustion chamber according to claim 1, characterized in that: The number of the mixing cooling air inlet and the supplementary combustion air inlet are both multiple, and are evenly distributed in the rear section cavity in the circumferential direction.

3. The low NOx hydrogen combustion chamber according to claim 1, characterized in that: Throats are formed between the injection ring and the combustion chamber inner ring and the combustion chamber inner ring on both sides, respectively, so that the air entering from the main air inlet enters the main flow channel annular cavity after being throttled by the throat.

4. A gas turbine, characterized in that: comprising a compressor, a low NOx hydrogen combustor as claimed in any one of claims 1 to 3, and a turbine; The compressor is coaxially connected to the turbine, air is introduced into the air inlet of the compressor, the air outlet of the compressor is connected to the low NOx hydrogen combustion chamber, and the flue gas outlet of the low NOx hydrogen combustion chamber is connected to the turbine, so that the flue gas generated by combustion drives the turbine to do work.

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