CN117628535A - Staged combustion method for hydrogen gas turbine and hydrogen gas turbine - Google Patents
Staged combustion method for hydrogen gas turbine and hydrogen gas turbine Download PDFInfo
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- 238000009841 combustion method Methods 0.000 title claims abstract description 27
- 239000000446 fuel Substances 0.000 claims abstract description 95
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- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 claims abstract description 26
- 239000003063 flame retardant Substances 0.000 claims abstract description 26
- 239000001257 hydrogen Substances 0.000 claims description 44
- 229910052739 hydrogen Inorganic materials 0.000 claims description 44
- 238000002156 mixing Methods 0.000 claims description 19
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 16
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 16
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- 206010016754 Flashback Diseases 0.000 description 2
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Abstract
The invention discloses a hydrogen gas turbine staged combustion method and a hydrogen gas turbine, comprising the following steps: after the flame-retardant gas is replaced in the ignition stage burner, introducing fuel into the ignition stage burner and igniting to generate ignition stage flame; after flame-retardant gas is replaced in the duty-stage burner, introducing fuel into the duty-stage burner and igniting by utilizing ignition-stage flame to generate duty-stage flame; after the ignition stage flame is closed, introducing flame-retardant gas into the ignition stage burner again, and keeping the combustion of the class flame; gradually increasing the flow of fuel introduced into the duty burner; after the flame-retardant gas is replaced in the main combustion stage burner, introducing fuel into the main combustion stage burner and igniting by using the pilot flame to generate micro-mixed premixed flame; combustion of the pilot flame and the micro-mix premix flame is maintained. The staged combustion method of the invention ensures that the hydrogen gas turbine has better combustion stability under the low-load working condition, and improves the conditions of thermal acoustic vibration such as combustion pulsation and the like.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a hydrogen-fuel gas turbine staged combustion method and a hydrogen gas turbine.
Background
Along with the acceleration of the global carbon neutralization process, the gas turbine with the hydrogen burning capability is the focus of the research and development of various current gas turbine manufacturers, and the development of the hydrogen gas turbine can relieve the energy safety problem on one hand, and can lead the application direction of the zero-carbon clean energy on the other hand, thereby playing a key supporting role in the construction of a novel power system taking new energy as a main body.
Compared with natural gas fuel based on methane used by a traditional gas turbine, the physical and chemical properties of hydrogen fuel are greatly different: (1) firstly, under the same condition, the unit volume heat value of the hydrogen is about one third of that of the natural gas, and higher volume flow and flow speed are needed to keep the same energy flow, so that the combustor through-flow design needs to be matched with the same; (2) the combustible limit range of the hydrogen is very wide, compared with the combustible equivalent ratio range of 0.40-1.50 of methane under the condition of normal temperature and normal pressure, the range of the hydrogen can be widened to 0.10-8.0, and the method also brings challenges to the traditional swirl lean premixed combustion tissue mode; (3) hydrogen is easy to self-ignite, the self-ignition delay time is very short and the minimum ignition energy is only 02mJ, and compared with 0.28mJ of methane, the hydrogen is as low as 14 times, and the blending and combustion process are more difficult to control; (4) the adiabatic flame temperature of the hydrogen can be 100-200 degrees higher than that of methane, and the emission control difficulty of NOx pollutants is increased sharply; (5) the flame propagation speed of hydrogen is very high, and the laminar flame propagation speed of the hydrogen can be up to 10 times of that of methane under the condition of normal temperature and normal pressure, and the hydrogen is extremely easy to temper.
In addition to optimizing or changing its premix burner to reduce flashback risk, the currently mainstream dry low emission premixed combustion organization mode combustion engine also requires adjustments in its combustion organization mode under different workload conditions to take corresponding countermeasures against the hydrogen fuel combustion flash back, deflagration, and high NOx emissions problems described above.
To solve the above problems, the publication shows that a relatively large number of combustion modes are adopted for the hydrogen fuel for combustion in the gas turbine in the related art, such as the micro-mixing burner described in CN110440290a, and the main feature is that the nozzle at the head of the micro-mixing burner is composed of a large number of mixing tube bundles, and the multi-tube bundle nozzle can form micro-scale mixing, so that the fuel and air can be uniformly mixed, the flame surface can be dispersed, the local heat load can be reduced, and the pollutant emission can be reduced.
However, the micro-mixed combustion organization mode is an improvement on the unit burner, the NOx emission performance and the fuel adaptability are improved at the expense of flame stability, jet flames generated by the micro-mixed burner lack a backflow area, the low-load combustion stability is obviously inferior to that of the traditional natural gas turbine swirl flames, and the thermoacoustic oscillation performance is unknown. The combustion stability of the gas turbine is poor under the working conditions of ignition, rotational speed rising, no-load and low load of the gas turbine in the running process of the gas turbine, and the problem of thermoacoustic vibration such as combustion pulsation exists, so that the working condition range is narrow only by adopting a micro-mixed combustion organization mode, and the excellent characteristic of the gas turbine can be shown only under high load.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems in the related art to some extent.
Therefore, the embodiment of the invention provides a staged combustion method of a hydrogen gas turbine, which ensures that the hydrogen gas turbine has better combustion stability under the working conditions of ignition, rotational speed rise, no-load and low load, improves the condition of thermal acoustic oscillation such as combustion pulsation, and the like, ensures that the hydrogen gas turbine also has better excellent operation characteristic under low load, avoids the problems of easy tempering and deflagration in the ignition process, and improves the use safety.
The embodiment of the invention also provides a hydrogen gas turbine adopting the staged combustion method.
The staged combustion method of the hydrogen gas turbine comprises the following steps of:
s1: after the flame-retardant gas is replaced in the ignition stage burner, introducing fuel into the ignition stage burner and igniting to generate an ignition stage flame;
s2: after flame-retardant gas is replaced in the duty-stage burner, introducing fuel into the duty-stage burner and igniting by utilizing the ignition-stage flame to generate duty-stage flame;
s3: after the ignition stage flame is closed, introducing flame-retardant gas into the ignition stage burner again, and keeping the combustion of the duty stage flame;
s4: gradually increasing the flow of fuel introduced into the duty-stage combustor to achieve warming-up and rotating up the hydrogen gas turbine to a rated idle rotation speed;
s5: after flame-retardant gas is replaced in the main combustion stage burner, introducing fuel into the main combustion stage burner and igniting by utilizing the duty stage flame to generate micro-mixed premixed flame;
s6: and maintaining the combustion of the duty-stage flame and the micro-mixed premixed flame to realize the operation of the hydrogen gas turbine under different loads.
The staged combustion method of the hydrogen gas turbine provided by the embodiment of the invention ensures that the hydrogen gas turbine has better combustion stability under the working conditions of ignition, rotational speed rise, no-load and low load, improves the condition of thermal acoustic shock such as combustion pulsation, ensures that the hydrogen gas turbine also has better excellent operation characteristic under low load, avoids the problems of easy tempering and deflagration in the ignition process, and improves the use safety.
In some embodiments, in the step S6, the operation of the hydrogen turbine under different loads is achieved by adjusting the fuel split ratio of the duty stage burner and the main gas burner while raising the total flow of fuel of the hydrogen turbine.
In some embodiments, when the hydrogen-fuelled gas turbine is operating at high load, the proportion of fuel introduced into the main stage combustor to the total flow of fuel is not less than the proportion of fuel introduced into the duty stage combustor to the total flow of fuel.
In some embodiments, the staged combustion method includes: an ignition stage, a warm-up acceleration stage and a load-up stage;
the ignition stage includes a step S1 and a step S2, the warm-up acceleration stage includes a step S3 and a step S4, and the load-up stage includes a step S5 and a step S6.
In some embodiments, in the steps S1 to S4, the fuel is not introduced into the main stage burner.
In some embodiments, the flame retardant gas is nitrogen; and/or the fuel is hydrogen.
In some embodiments, the ignition stage burner, the duty stage burner, and the main stage burner each comprise a fuel line for enabling passage of fuel and a displacement line for displacing gas within the fuel line with the flame retardant gas when the fuel line is not being passed.
In some embodiments, in step S1, the fuel in the ignition stage combustor is ignited by a spark plug.
In some embodiments, the annular nozzle of the ignition stage burner surrounds the outer peripheral side of the duty stage burner, the spray holes of the duty stage burner are arranged at the end part of the duty stage burner and are distributed along the circumferential interval of the duty stage burner, and the spray holes of the main combustion stage burner are positioned at the inner side of each micro-mixing pipe of the main combustion stage burner and are perpendicular to the inner wall surface of the micro-mixing pipe.
The hydrogen gas turbine of the embodiment of the invention adopts the hydrogen gas turbine staged combustion method as described in any of the above embodiments.
Drawings
FIG. 1 is a schematic view of the structure of an ignition stage combustor, a duty stage combustor, and a main combustion stage combustor of a hydrogen gas turbine according to an embodiment of the present invention.
FIG. 2 is a schematic view of an ignition stage combustor, a duty stage combustor, a main combustion stage combustor of a hydrogen gas turbine of an embodiment of the invention at the end.
FIG. 3 is a schematic illustration of a combustion process of a hydrogen gas turbine in accordance with an embodiment of the present invention.
Reference numerals:
an ignition stage burner 1; an ignition stage annular nozzle 11;
an on duty burner 2; class nozzle 21;
a main stage burner 3; micro-mixing tube 31, main combustion stage nozzle 32.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
As shown in fig. 1, the staged combustion method of the hydrogen turbine of the embodiment of the present invention is based on a hydrogen turbine having three combustion stages of an ignition stage, a shift stage, and a main combustion stage, and is mainly directed to a hydrogen turbine in which fuel is hydrogen. As shown in fig. 2, the ignition stage may be specifically referred to as a torch ignition stage (ignition stage burner 1), the duty stage may be specifically referred to as a pilot value shift (duty stage burner 2), the main combustion stage may be specifically referred to as a main combustion stage (main combustion stage burner 3), wherein both the ignition stage and the value shift may be in a diffusion combustion organization mode, and the main combustion stage may be in a micro-mix premixed combustion organization mode.
The ignition stage burner 1, the duty stage burner 2 and the main combustion stage burner 3 each include a fuel line and a substitution line, wherein the fuel line is used for realizing the fuel passing in each combustion stage, so that the use requirements of ignition and combustion can be realized. The replacement pipeline is used for replacing the gas in the fuel pipeline with flame-retardant gas when fuel is not filled in the fuel pipeline.
On the basis of the hydrogen gas turbine, the staged combustion method mainly comprises the following steps:
s1: after the flame retardant gas is displaced in the ignition stage burner 1, fuel is introduced into the ignition stage burner 1 and ignited to generate an ignition stage flame. Specifically, as shown in fig. 1 and fig. 2, before the ignition stage combustor 1 ignites, a flame retardant gas, which may specifically be nitrogen, may be first introduced into the fuel line of the ignition stage combustor 1, and in other embodiments, other gases having flame retardant effects may also be used.
After the flame-retardant gas is introduced for a certain time, hydrogen can be introduced into the fuel pipeline of the ignition stage combustor 1, then the fuel of the ignition stage combustor 1 can be ignited by utilizing a spark plug, and the flame generated by ignition is the ignition stage flame, and the flame is diffusion flame, as shown in a (a) diagram in fig. 3.
The air in the fuel line of the ignition stage burner 1 can be discharged by introducing the flame retardant gas, so that the hydrogen gas can be prevented from being easily mixed with the air to cause spontaneous combustion after being introduced into the fuel line.
S2: after the flame retardant gas is replaced in the duty burner 2, fuel is introduced into the duty burner 2 and ignited by the ignition stage flame to generate the duty flame.
Specifically, after the ignition stage flame is ignited, a stable duty stage flame can be established, and during the establishment, nitrogen can be firstly introduced into the fuel pipeline of the duty stage burner 2, so that the replacement of air in the fuel pipeline of the duty stage burner 2 can be realized, and the situation that the container is self-ignited when hydrogen is introduced into the fuel pipeline is avoided.
After nitrogen in the fuel pipeline of the class is introduced for a certain time, hydrogen can be introduced into the fuel pipeline, the introduced hydrogen can be ignited by means of an ignition stage flame, and the flame ignited at the class is the class flame, specifically, as shown in a (b) diagram in fig. 3. Therefore, ignition of the ignition stage flame in the diffusion combustion mode to the duty stage flame in the diffusion combustion mode is realized, and ignition operation is facilitated.
S3: after the ignition stage flame is closed, flame-retardant gas is introduced into the ignition stage combustor 1 again, so that the combustion of the valve class flame is maintained.
Specifically, after the on-duty flame is ignited, the ignition stage flame can be closed, namely the supply of fuel in the fuel pipeline of the ignition stage combustor 1 can be cut off, and after the ignition stage flame is extinguished, nitrogen can be introduced into the fuel pipeline of the ignition stage again, so that the replacement of the fuel pipeline of the ignition stage can be realized, and the flame-retardant isolation effect is achieved.
After the ignition-level flame is extinguished, only the combustion of the duty-level flame can be kept, and at the moment, an independent diffusion combustion mode of the duty-level flame is entered.
S4: the flow of fuel to the shift burner 2 is stepped up to achieve warm-up and to increase the speed of the hydrogen turbine to the nominal idle speed. Specifically, after the on-duty flame is independently combusted, the inflow rate of fuel in the fuel pipeline of the on-duty stage can be gradually increased, so that the warming-up operation of the hydrogen gas turbine can be realized, the rotating speed of the hydrogen gas turbine can be simultaneously increased to the rated idle rotating speed, the stable increase of the rotating speed is realized, and the load of the on-duty stage combustor 2 can be increased to the maximum load of the on-duty stage.
The process of increasing the rotational speed of the hydrogen turbine to the rated idling rotational speed and the process of increasing the duty burner 2 to the duty maximum load may be two independent processes, for example, the rated idling rotational speed of the hydrogen turbine may be first increased to the rated idling rotational speed by increasing the fuel flow, as shown in fig. 3 (c). The fuel flow may then continue to be increased so that the duty of the duty cycle burner 2 may be increased to the duty cycle maximum load, as shown particularly in fig. 3 (d). Thereby ensuring stability and relative independence in the process of speed up and load up.
In the process of increasing the rotating speed and increasing the load to the maximum load of the duty stage, only the flame of the duty stage works independently, so that the overall controllability of the flame of the duty stage is good, and the problem of unstable combustion of the central micro-mixing premixed combustion organization mode in the prior art under low load can be effectively solved.
S5: after the flame retardant gas is displaced in the main stage burner 3, fuel is introduced into the main stage burner 3 and ignited with a pilot flame to generate a micro-mixed premixed flame.
Specifically, after the speed raising of the hydrogen gas turbine is completed, the independent combustion work of the duty-stage flame can be continuously maintained, meanwhile, nitrogen can be introduced into the fuel pipeline of the main combustion stage combustor 3, so that the replacement of air in the fuel pipeline can be realized, after the nitrogen is introduced for a certain time, hydrogen can be introduced into the fuel pipeline of the main combustion stage combustor 3, the hydrogen introduced by the main combustion stage can be ignited by the duty-stage flame, and the flame generated by the ignited hydrogen is a micro-mixed premixed flame (main combustion stage flame), as shown in a (e) diagram in fig. 3. Thereby achieving the ignition of the diffusion combustion flame to the premixed combustion flame.
It should be noted that, the nozzle of the main stage burner 3 according to the embodiment of the present invention may be composed of a large number of mixing tube bundles, and the multi-tube bundle nozzle may form micro-scale mixing, so that the fuel air is uniformly mixed, and the flame generated by the nozzle formed by the mixing tube bundles is the micro-mixing premixed flame.
S6: combustion of the pilot flame and the micro-mix premix flame is maintained to achieve operation of the hydrogen turbine at different loads. The hydrogen gas turbine can simultaneously maintain simultaneous combustion of the duty-level flame and the micro-mixed premixed flame in the operation process of the hydrogen gas turbine, namely hydrogen needs to be simultaneously introduced into fuel pipelines of the duty-level flame and the main combustion level flame, the two flames can form a complementary relationship, and particularly, under high load of the hydrogen gas turbine, a working mode taking main combustion level micro-mixed premixed combustion (micro-mixed premixed flame) as a main mode and pilot duty-level diffusion (duty-level flame) as an auxiliary mode can be formed, so that excellent low NOx emission characteristics of the micro-mixed premixed combustion under high load can be exerted.
The staged combustion method of the hydrogen gas turbine provided by the embodiment of the invention ensures that the hydrogen gas turbine has better combustion stability under the working conditions of ignition, rotational speed rise, no-load and low load, improves the condition of thermal acoustic shock such as combustion pulsation, ensures that the hydrogen gas turbine also has better excellent operation characteristic under low load, avoids the problems of easy tempering and deflagration in the ignition process, and improves the use safety.
In some embodiments, in step S6, operation of the hydrogen turbine at different loads is achieved by adjusting the fuel split ratio of the duty stage combustor 2 and the main engine combustor while increasing the total flow of fuel to the hydrogen turbine. Specifically, when the overall operating load of the hydrogen turbine decreases, the fuel ratio of the main stage combustor 3 may be adjusted down, while the fuel ratio of the on-duty stage combustor 2 may be adjusted up. When the load of the whole working condition of the hydrogen gas turbine is increased, the fuel proportion of the main combustion stage combustor 3 can be increased, and meanwhile, the fuel proportion of the duty stage combustor 2 can be reduced. Therefore, the combustion working condition filtering under different loads can be realized through the fuel inflow adjustment of the two combustion stages, and the stability of switching between different working conditions are improved.
In some embodiments, when the hydrogen-fuelled gas turbine is operating at high load, the proportion of fuel admitted to the main stage burner 3 to the total flow of fuel is not less than the proportion of fuel admitted to the duty stage burner 2 to the total flow of fuel. For example, when operating at high load, the fuel in the fuel line of the main stage may be 70% and the fuel in the fuel line of the duty stage burner 2 may be 30%. Thus ensuring low pollutant emission of the whole combustion under high load.
In some embodiments, the staged combustion method includes: an ignition stage, a warm-up ramp-up stage, and a load-up stage, wherein the ignition stage may include step S1 and step S2, the warm-up ramp-up stage may include step S3 and step S4, and the load-up stage may include step S5 and step S6. Therefore, the regulation and control requirements of combustion in different stages are realized, and more accurate and efficient regulation and control can be realized in a staged mode.
In some embodiments, in steps S1 to S4, no fuel is introduced into the main stage burner 3. Therefore, the problems of tempering and deflagration caused by premixed spontaneous combustion in the ignition process and more serious combustion safety caused by potential deflagration to detonation can be effectively avoided.
In some embodiments, as shown in fig. 1, the nozzle of the ignition stage burner 1 and the nozzle of the duty stage burner 2 may be pillar-shaped, wherein the nozzle of the ignition stage burner 1 (ignition stage annular nozzle 11) may be annular and surround the outer peripheral side of the duty stage burner 2, and the nozzle holes of the duty stage burner 2 (duty stage nozzle holes 21) are provided at the end of the duty stage burner and uniformly arranged along the circumference of the end of the duty stage combustion. Therefore, when the ignition-stage flame is ignited, the ignition-stage flame can be sprayed to the spray hole of the duty-stage burner 2, so that the ignition of the duty-stage flame is facilitated.
In some embodiments, as shown in fig. 1, the nozzle portion of the main combustion stage combustor 3 may be formed by stacking a plurality of micro-mixing pipes 31, and the stacked whole body is annular, a plurality of main combustion stage spray holes 32 may be disposed on the pipe wall of each micro-mixing pipe 31, the main combustion stage spray holes 32 may be located on the inner side of the micro-mixing pipe 31, and the extending direction of each main combustion stage spray hole 32 may be perpendicular to the inner wall surface of the corresponding micro-mixing pipe 31, so that fuel is conveniently sprayed out along the radial direction, and ignition is further facilitated.
The following describes a hydrogen gas turbine according to an embodiment of the present invention.
The hydrogen gas turbine of the embodiment of the invention comprises three combustion stages of an ignition stage, a pilot stage and a main combustion stage, and adopts the staged combustion method as described in any of the above embodiments in operation.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While the above embodiments have been shown and described, it should be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the invention.
Claims (10)
1. A staged combustion method for a hydrogen gas turbine, comprising the steps of:
s1: after the flame-retardant gas is replaced in the ignition stage burner, introducing fuel into the ignition stage burner and igniting to generate an ignition stage flame;
s2: after flame-retardant gas is replaced in the duty-stage burner, introducing fuel into the duty-stage burner and igniting by utilizing the ignition-stage flame to generate duty-stage flame;
s3: after the ignition stage flame is closed, introducing flame-retardant gas into the ignition stage burner again, and keeping the combustion of the duty stage flame;
s4: gradually increasing the flow of fuel introduced into the duty-stage combustor to achieve warming-up and rotating up the hydrogen gas turbine to a rated idle rotation speed;
s5: after flame-retardant gas is replaced in the main combustion stage burner, introducing fuel into the main combustion stage burner and igniting by utilizing the duty stage flame to generate micro-mixed premixed flame;
s6: and maintaining the combustion of the duty-stage flame and the micro-mixed premixed flame to realize the operation of the hydrogen gas turbine under different loads.
2. The hydrogen turbine staged combustion method as claimed in claim 1, wherein in step S6, operation of the hydrogen turbine at different loads is achieved by adjusting fuel split ratios of the duty burner and the main burner while raising total flow of fuel to the hydrogen turbine.
3. The staged combustion method of a hydrogen gas turbine as claimed in claim 2, wherein the proportion of fuel introduced into the main stage burner to the total flow of fuel is not less than the proportion of fuel introduced into the duty stage burner to the total flow of fuel when the hydrogen gas turbine is operated at high load.
4. The hydrogen turbine staged combustion method as claimed in claim 3, wherein the staged combustion method comprises: an ignition stage, a warm-up acceleration stage and a load-up stage;
the ignition stage includes a step S1 and a step S2, the warm-up acceleration stage includes a step S3 and a step S4, and the load-up stage includes a step S5 and a step S6.
5. The hydrogen turbine staged combustion method as claimed in claim 1, wherein in steps S1 to S4, the fuel is not fed to the primary stage burner.
6. The hydrogen gas turbine staged combustion method of claim 1, wherein the flame retardant gas is nitrogen; and/or the fuel is hydrogen.
7. The staged combustion method of a hydrogen turbine as claimed in claim 1, wherein the ignition stage burner, the duty stage burner, and the main stage burner each comprise a fuel line for effecting passage of fuel and a substitution line for substituting the gas in the fuel line for the flame retardant gas when the fuel line is not passed.
8. The hydrogen turbine staged combustion method as claimed in claim 1, wherein in step S1, the fuel in the ignition stage burner is ignited by a spark plug.
9. The staged combustion method of a hydrogen turbine as claimed in any one of claims 1 to 8, wherein the annular nozzle of the ignition stage burner is surrounded on the outer peripheral side of the duty stage burner, the nozzle holes of the duty stage burner are arranged at the end of the duty stage burner and are arranged at intervals along the circumferential direction of the duty stage burner, and the nozzle holes of the main stage burner are positioned on the inner side of each micro-mixing tube of the main stage burner and are perpendicular to the inner wall surface of the micro-mixing tube.
10. A hydrogen gas turbine comprising a staged combustion method of a hydrogen gas turbine as claimed in any of the claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311519921.4A CN117628535A (en) | 2023-11-15 | 2023-11-15 | Staged combustion method for hydrogen gas turbine and hydrogen gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311519921.4A CN117628535A (en) | 2023-11-15 | 2023-11-15 | Staged combustion method for hydrogen gas turbine and hydrogen gas turbine |
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| Publication Number | Publication Date |
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| CN117628535A true CN117628535A (en) | 2024-03-01 |
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| CN202311519921.4A Pending CN117628535A (en) | 2023-11-15 | 2023-11-15 | Staged combustion method for hydrogen gas turbine and hydrogen gas turbine |
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