CN115325569B - Combustion chamber, gas turbine and combustion control method - Google Patents
Combustion chamber, gas turbine and combustion control method Download PDFInfo
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- CN115325569B CN115325569B CN202211075964.3A CN202211075964A CN115325569B CN 115325569 B CN115325569 B CN 115325569B CN 202211075964 A CN202211075964 A CN 202211075964A CN 115325569 B CN115325569 B CN 115325569B
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- hydrogen
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 108
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000009792 diffusion process Methods 0.000 claims abstract description 50
- 239000000446 fuel Substances 0.000 claims abstract description 35
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 75
- 239000001257 hydrogen Substances 0.000 claims description 70
- 229910052739 hydrogen Inorganic materials 0.000 claims description 70
- 239000007789 gas Substances 0.000 claims description 63
- 238000002156 mixing Methods 0.000 claims description 8
- 238000001816 cooling Methods 0.000 claims description 6
- 238000010791 quenching Methods 0.000 claims description 5
- 230000000171 quenching effect Effects 0.000 claims description 5
- 230000009471 action Effects 0.000 abstract description 6
- 238000010008 shearing Methods 0.000 abstract description 4
- 230000002159 abnormal effect Effects 0.000 abstract description 2
- 230000010349 pulsation Effects 0.000 abstract description 2
- 230000000712 assembly Effects 0.000 description 12
- 238000000429 assembly Methods 0.000 description 12
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 8
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 6
- 239000003345 natural gas Substances 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000003570 air Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
The invention relates to the technical field of gas turbines, in particular to a combustion chamber, a gas turbine and a combustion control method, wherein the combustion chamber comprises: a cylinder body having a cavity providing a combustion space; the combustion chamber head section is connected with the barrel, includes: at least one nozzle assembly and at least one diffusion assembly; the nozzle component and the diffusion component are sleeved at intervals; the gas turbine includes a combustor; by adopting the scheme, the flow velocity of the diffusion gas generated by the diffusion component is lower than the flow velocity of the premixed gas sprayed from the nozzle component, and the strong shearing action between the boundary layers of the diffusion component and the nozzle component reduces the flow velocity of the premixed gas sprayed from the nozzle component, so that the combustion flame is more stable; thereby improving the operating efficiency and stability of the gas turbine. The combustion control method includes: after the fuel conveyed to the cylinder body by the diffusion component burns stably, the fuel is conveyed into the cylinder body by the nozzle component to burn; the method ensures that the combustion is always in a stable state, and avoids over-temperature and abnormal pressure pulsation.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustion chamber, a gas turbine and a combustion control method.
Background
Currently, gas turbines are widely used in various industries such as energy, electricity, and ships. The hydrogen energy is rapidly developed due to the advantages of cleanness, environmental protection, sustainable utilization and the like, and is widely applied to the fields of traffic, chemical industry and the like. The existing natural gas hydrogen-adding combustion technology is to add a certain proportion of hydrogen into natural gas, and then to convey the mixed gas to a combustion chamber of a gas turbine for combustion after the mixed gas is uniformly mixed. The natural gas hydrogen-doped combustion technology can ensure the power generation efficiency of the gas turbine combined cycle unit and reduce carbon emission.
The heat value of the hydrogen is high, and the combustion product is only water, so that the method is particularly suitable for combustion of a gas turbine. The combustion mode of the gas turbine comprises: premixed combustion and diffusion combustion. However, the hydrogen premixed combustion has high combustion speed and is easy to temper; the diffusion combustion causes the local temperature of the combustion zone to be too high, so that the emission of nitrogen oxides is increased, and the temperature distribution uniformity of the outlet of the combustion chamber is poor.
Disclosure of Invention
Therefore, the invention aims to overcome the defects of easy tempering and unstable combustion in the prior art of hydrogen premixed combustion.
In order to achieve the above object, the present invention provides a combustion chamber comprising:
a cylinder body having a cavity providing a combustion space;
a combustion chamber head section connected to the barrel, comprising: at least one nozzle assembly and at least one diffusion assembly; the nozzle component and the diffusion component are sleeved at intervals.
Optionally, the nozzle assembly comprises:
the nozzle body is used for conveying premixed fuel to the cylinder body, the nozzle of the nozzle body is a circular seam, and the width of the circular seam is smaller than the quenching distance of hydrogen;
and the premix gas supply part is connected with the nozzle body and is used for conveying premix fuel to the nozzle body.
Optionally, the nozzle assembly further includes a fixing plate, a plurality of strip-shaped channels are disposed on the fixing plate, and the fixing plate is disposed in the premixed gas supply member, so that the premixed gas supply member is divided into a main gas supply cavity and a plurality of branch gas supply cavities correspondingly disposed, and the plurality of branch gas supply cavities and the plurality of strip-shaped channels are disposed in one-to-one correspondence.
Optionally, the diffusion assembly comprises:
an air supply channel communicated with the inside of the cylinder, wherein a cyclone is arranged at one end of the air supply channel close to the cylinder;
the hydrogen supply channel is sleeved with the air supply channel, the hydrogen supply channel is communicated with the inside of the cylinder body, and a hydrogen supply hole is formed in one end, close to the cylinder body, of the hydrogen supply channel.
Optionally, the swirlers in adjacent air supply channels are of opposite sense.
Optionally, the hydrogen supply hole is arranged at an angle to the axial direction of the hydrogen supply channel, the hydrogen supply hole is inclined to the axial direction of the combustion chamber, and the angle between the axial direction of the hydrogen supply hole and the axial direction of the hydrogen supply channel is 30-60 degrees.
Optionally, a plurality of cooling holes are provided on the outer wall of the cylinder.
Optionally, a plurality of mixing holes are provided in the end of the barrel remote from the combustion chamber head section.
The invention also provides a gas turbine comprising the combustion chamber.
The invention also provides a combustion control method, which uses the combustion chamber to burn, comprising the following steps: after the fuel delivered to the cylinder body through the diffusion component burns stably, the fuel is delivered into the cylinder body through the nozzle component, so that the fuel burns.
Compared with the prior art, the technical scheme of the invention has the following advantages:
1. the present invention provides a combustion chamber comprising: a cylinder body having a cavity providing a combustion space; a combustion chamber head section connected to the barrel, comprising: at least one nozzle assembly and at least one diffusion assembly; the nozzle component and the diffusion component are sleeved at intervals; according to the technical scheme, the nozzle assembly and the diffusion assembly are sleeved at intervals, the flow velocity of diffusion gas generated by the diffusion assembly is lower than that of premixed gas sprayed out of the nozzle assembly, and the flow velocity of premixed gas sprayed out of the nozzle assembly can be reduced due to the strong shearing action between boundary layers of the nozzle assembly and the diffusion assembly, so that combustion flame is more stable; meanwhile, the emission of nitrogen oxides is reduced, and the uniformity of the temperature distribution of the outlet of the combustion chamber is improved.
2. The nozzle assembly of the present invention comprises: the nozzle body is used for conveying premixed fuel to the cylinder body, the nozzle of the nozzle body is a circular seam, and the width of the circular seam is smaller than the quenching distance of hydrogen; a premix gas supply connected to the nozzle body for delivering premix fuel to the nozzle body; according to the technical scheme, the width of the circumferential seam is smaller than the quenching distance of hydrogen, when flame reversely burns upstream along the circumferential seam, the narrow flow channel can increase heat loss of fuel combustion, meanwhile, the collision probability of free radicals and the wall surface of the flow channel is increased, the free radicals participating in the reaction are reduced, so that combustion is stopped, and backfire is prevented.
3. The nozzle assembly further comprises a fixing plate, wherein a plurality of strip-shaped channels are arranged on the fixing plate, the fixing plate is arranged in the premixed gas supply part to divide the premixed gas supply part into a main gas supply cavity and a plurality of branch gas supply cavities which are correspondingly arranged, and the plurality of branch gas supply cavities are correspondingly arranged one by one with the plurality of strip-shaped channels; the application adopts above-mentioned technical scheme, carries out reliable fixed connection with the nozzle assembly through the fixed plate.
4. The diffusion assembly of the present invention comprises: an air supply channel communicated with the inside of the cylinder, wherein a cyclone is arranged at one end of the air supply channel close to the cylinder; the hydrogen supply channel is sleeved with the air supply channel, is communicated with the inside of the cylinder body, and is provided with a hydrogen supply hole at one end, close to the cylinder body, of the hydrogen supply channel; according to the hydrogen gas and air stable swirl flow device, due to the fact that the density and the flow rate of air are high, a reasonable backflow area is obtained, hydrogen gas can flow downstream along with air at a certain swirl angle through interaction of the hydrogen gas and the air, and the swirler can be connected with and fixed to an adjacent nozzle assembly and a diffusion assembly; meanwhile, hydrogen is used as fuel, so that carbon emission can be effectively reduced, and the environment is protected.
5. The swirlers in adjacent air supply channels of the invention are opposite in rotation direction; the cyclone with opposite rotation directions is favorable for forming a reasonable backflow area, enhances interaction of a boundary layer between diffusion gas and premixed gas sprayed from the nozzle assembly, reduces flow velocity of the premixed gas, and stabilizes flame.
6. The hydrogen supply hole and the axial direction of the hydrogen supply channel are arranged at an angle, the hydrogen supply hole is inclined to the axial direction of the combustion chamber, and the axial angle between the hydrogen supply hole and the axial direction of the hydrogen supply channel is 30-60 degrees; by adopting the technical scheme, the application ensures that after the hydrogen flows out from the hydrogen supply hole, the hydrogen can enter the main flow area of diffusion air, and is favorable for mixing the hydrogen and the air and diffusion combustion.
7. The invention is provided with a plurality of cooling holes on the outer wall of the cylinder; the application reduces through setting up the cooling hole the wall temperature of barrel.
8. The invention is provided with a plurality of mixing holes at one end of the cylinder body far away from the head section of the combustion chamber; the application adjusts the distribution of the outlet temperature of the combustion chamber by arranging the mixing holes.
9. The gas turbine provided by the invention comprises the combustion chamber; the structure setting through the combustion chamber is adopted in this application for the combustion flame is more stable, and then improves gas turbine's operating efficiency and stability.
10. The combustion control method provided by the invention utilizes the combustion chamber to burn, and comprises the following steps: after the fuel conveyed to the cylinder body by the diffusion component burns stably, the fuel is conveyed into the cylinder body by the nozzle component to burn; by adopting the technical scheme, the combustion can be ensured to be always in a stable state, and the overtemperature and abnormal pressure pulsation phenomenon are avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic perspective view of a combustion chamber according to an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of a combustion chamber provided in an embodiment of the present invention;
FIG. 3 is a schematic right-side view of a combustion chamber provided in an embodiment of the present invention;
FIG. 4 is a schematic view of a partial enlarged structure at A in FIG. 2;
FIG. 5 is a schematic view of a partial enlarged structure at B in FIG. 2;
FIG. 6 is a schematic view of a partial enlarged structure at C in FIG. 2;
fig. 7 is a schematic view showing a partial sectional structure of a combustion chamber according to an embodiment of the present invention.
Reference numerals illustrate:
1. a combustion chamber head section; 2. a cylinder; 3. a main air supply chamber; 4. a branch air supply cavity; 5. a radial fixing plate; 6. an axial fixing plate; 7. a nozzle body; 8. an air supply passage; 9. a hydrogen supply passage; 10. a cyclone; 11. a hydrogen supply hole; 12. a cooling hole; 13. a blending hole; 14. a strip-shaped channel; 15. and a fixing plate.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
One embodiment of the combustion chamber as shown in fig. 1 to 7 comprises: a combustion chamber head section 1 and a cylinder body 2 which are connected in sequence.
As shown in fig. 1 to 3 and fig. 7, the cylinder 2 has a cavity providing a combustion space, i.e., a flame tube; the combustion chamber head section 1 includes: the three nozzle assemblies and the three diffusion assemblies are sequentially sleeved at intervals. The three nozzle assemblies and the three diffusion assemblies are coaxially and circumferentially arranged in six stages. Further, the number of stages of arrangement can be appropriately adjusted by the design dimensions of the combustion chamber and the combustion design parameters.
The nozzle assembly includes: a nozzle body 7, a premixed gas supply member, and a fixing plate 15, wherein the nozzle body 7 is used for delivering premixed fuel to the cylinder 2, and specifically, the premixed fuel is mixed fuel of natural gas, hydrogen and air, or mixed fuel of hydrogen and air; the nozzle of the nozzle body 7 is a circular seam, and the width of the circular seam is smaller than the quenching distance of hydrogen; the premix gas supply is connected to the nozzle body 7 for delivering premix fuel to the nozzle body 7. The fixing plate 15 is ring-shaped, as shown in fig. 7, and the fixing plate 15 includes: a radial fixing plate 5 and an axial fixing plate 6 connected to each other; specifically, the cross section of the axial fixing plate 6 is in a circular shape, the radial fixing plates 5 are connected with five axial fixing plates 6, two adjacent radial fixing plates 5 and two axial fixing plates 6 form a strip-shaped channel 14, further, the area of the strip-shaped channel 14 can be properly adjusted according to combustion design parameters and required flow, the areas of the strip-shaped channels 14 are different, and the flow is different; the fixing plate 15 is arranged in the premixed gas supply part to divide the premixed gas supply part into a main gas supply cavity 3 and a plurality of branch gas supply cavities 4 which are correspondingly arranged, and the plurality of branch gas supply cavities 4 are correspondingly arranged with the plurality of strip-shaped channels 14 one by one; specifically, the sections of the main air supply cavity 3 and the branch air supply cavity 4 are circular.
Each stage nozzle assembly includes: and each main air supply cavity 3 corresponds to four branch air supply cavities 4. Further, the number of the branch air supply cavities 4 of each stage of nozzle assembly can be appropriately adjusted according to the design size of the combustion chamber and combustion design parameters, and the specific combustion design parameters include: and the flow field parameters of the combustion chamber are distributed. The fuel flow in each stage of nozzle assembly and diffusion assembly may be individually regulated. Further, the flow rate of each air supply cavity 4 in each stage of nozzle assembly is independently adjusted; the flow rates of the air supply channel 8 and the hydrogen supply channel 9 in each stage of diffusion assembly are also all supported for independent adjustment. The fuel inlet and the fuel outlet of the nozzle assembly are provided with round corners so as to reduce resistance loss; the internal connection of the combustion chamber head section 1 and the cylinder body 2 is provided with a rounding corner, so that an angular backflow area is avoided.
As shown in fig. 4 to 6, the diffusion assembly includes: an air supply passage 8 and a hydrogen supply passage 9; the air supply channel 8 is communicated with the inside of the cylinder 2, and a cyclone 10 is arranged at the right end of the air supply channel 8; the swirlers 10 in adjacent air supply channels 8 are of opposite sense; further, the larger the diameter of the diffusion component, the more the blades of the cyclone 10, and the blade size of the cyclone 10 can be properly adjusted according to the combustion design parameters to ensure the swirling effect. The hydrogen supply channel 9 is sleeved with the air supply channel 8, the hydrogen supply channel 9 is communicated with the inside of the cylinder 2, and a hydrogen supply hole 11 is formed in the right end of the hydrogen supply channel 9. The hydrogen gas supply hole 11 is arranged at an angle to the axial direction of the hydrogen gas supply passage 9; the hydrogen supply hole 11 is inclined towards the axial direction of the combustion chamber, the axial direction of the hydrogen supply hole 11 and the axial direction of the hydrogen supply channel 9 are in an angle range of 30-60 degrees, and the specific angle can be properly adjusted according to combustion design parameters so as to ensure the swirling effect. Specifically, the hydrogen supply holes 11 are circumferentially distributed at the end of the hydrogen supply passage 9; further, the number and diameter of the hydrogen gas supply holes 11 can be appropriately adjusted. Each stage of diffusion assembly comprises: a single air supply channel 8 and a hydrogen supply channel 9. Specifically, the cross section of the air supply channel 8 is circular; the central stage is a hydrogen supply channel 9 and is a cylindrical cavity; the hydrogen supply channels 9 of the remaining stages are also circular in cross section.
A plurality of cooling holes 12 are provided in the outer wall of the cylinder 2. A plurality of mixing holes 13 are provided at the right end of the cylinder 2.
The invention also provides a gas turbine comprising the combustion chamber.
The invention also provides a combustion control method, which uses the combustion chamber to burn, comprising the following steps: after the fuel delivered to the cylinder body through the diffusion component burns stably, the fuel is delivered into the cylinder body through the nozzle component, so that the fuel burns. When a certain level of nozzle assembly is used for gas supply combustion, at least one level of diffusion assembly which is adjacent to the certain level of nozzle assembly is also used for gas supply combustion, so that combustion stability is ensured. Further, when the gas turbine is in the start-up stage, only part of the nozzle assemblies and the diffusion assemblies can be relied on to burn out the force; when the gas turbine operates at rated power, all the nozzle assemblies and the diffusion assemblies can be operated, so that the continuous and stable output of the gas turbine is ensured; when the machine is stopped, fuel supply of the nozzle assembly and the diffusion assembly can be stopped according to a sequence control program; in order to protect the safety of the gas turbine and its auxiliary equipment when the engine jumps due to a fault, the fuel supply to all nozzle assemblies and diffusion assemblies may be shut off in a sequence control program. Specifically, during shutdown, the fuel supply to the nozzle assembly should be stopped first, and after the gas turbine stabilizes, the fuel supply to the diffusion assembly should be stopped.
The combustion control process principle of the combustion chamber is briefly described as follows: in the flame tube, the area positioned at the downstream of the nozzle assembly outlet is used as a main combustion area, the area positioned at the downstream of the diffusion assembly outlet is used as a duty area, the duty flame is formed during the diffusion combustion of the hydrogen and the air, and the premixed gas of the hydrogen and the air sprayed out of the nozzle body 7 is ignited, so that the main combustion area is stably combusted. When the combustion chamber works, firstly, on-duty flame is stably combusted, the air supply channels 8 in each stage of diffusion assemblies convey air to the cyclone 10, and after directional cyclone is generated under the action of the cyclone 10, the air flows out of the air supply channels 8 and flows to the downstream of the combustion chamber at a certain cyclone angle. Simultaneously, the hydrogen supply channel 9 in each stage of diffusion assembly conveys hydrogen to the tail end of the diffusion assembly, and then the hydrogen is conveyed to the main air flow area in the flame tube by the hydrogen supply hole 11 at a certain angle, so that the hydrogen and the air are fully mixed; because of the high density and large flow of air and the action of gas jet, the hydrogen and the air have strong shearing action, so that the hydrogen flows along with the air to the downstream of the combustion chamber at the same rotational flow angle, a backflow area is formed, and an on-duty combustion area can be formed after ignition. After the flame on duty is stabilized, the premixed gas formed by uniformly mixing the hydrogen and the air flows into each stage of main gas supply cavities 3, then flows into each gas supply cavity 4 through the strip-shaped channels 14, and the premixed fuel is conveyed into the flame tube to be combusted by the corresponding nozzle body 7, so that a main combustion area is formed. In the initial stage of ignition, the combustion chamber can start to supply air and burn from the central stage diffusion assembly and the adjacent nozzle assemblies, and after the combustion is stable, hydrogen and air are supplied step by step along the radial direction, so that a multi-stage duty zone and a main combustion zone are formed step by step. The flow velocity of the diffusion gas in the duty zone is lower than that of the premixed gas sprayed from the nozzle body 7, so that the flow velocity of the premixed gas sprayed from the nozzle body 7 can be reduced under the strong shearing action between boundary layers of the diffusion gas and the premixed gas, and the flame in the main combustion zone is stabilized.
Alternatively, the main air supply chamber 3 is eliminated and premix fuel is supplied directly from the branch air supply chamber 4.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present invention.
Claims (8)
1. A combustion chamber, comprising:
a cylinder (2) having a cavity providing a combustion space;
a combustion chamber head section (1) connected with the cylinder (2), comprising: at least one nozzle assembly and at least one diffusion assembly; the nozzle component and the diffusion component are sleeved at intervals;
the nozzle assembly includes:
the nozzle body (7) is used for conveying premixed fuel to the cylinder body (2), the nozzle of the nozzle body (7) is a circular seam, and the width of the circular seam is smaller than the quenching distance of hydrogen;
a premix gas supply connected to the nozzle body (7) for delivering premix fuel to the nozzle body (7);
the diffusion assembly includes:
an air supply channel (8) communicated with the interior of the cylinder (2), and a cyclone (10) is arranged at one end of the air supply channel (8) close to the cylinder (2);
the hydrogen supply channel (9) is sleeved with the air supply channel (8), the hydrogen supply channel (9) is communicated with the inside of the cylinder body (2), and a hydrogen supply hole (11) is formed in one end, close to the cylinder body (2), of the hydrogen supply channel (9).
2. The combustor according to claim 1, wherein the nozzle assembly further comprises a fixing plate (15), a plurality of strip-shaped channels (14) are arranged on the fixing plate (15), the fixing plate (15) is arranged in the premixed gas supply part to divide the premixed gas supply part into a main gas supply cavity (3) and a plurality of branch gas supply cavities (4) which are correspondingly arranged, and the plurality of branch gas supply cavities (4) are correspondingly arranged one by one with the plurality of strip-shaped channels (14);
the fixing plate (15) includes: a radial fixing plate (5) and an axial fixing plate (6) connected with each other; the cross section of the axial fixing plate (6) is circular, the radial fixing plates (5) are connected with a plurality of axial fixing plates (6), and two adjacent radial fixing plates (5) and two axial fixing plates (6) form a strip-shaped channel 14.
3. A combustion chamber according to claim 1, characterized in that the swirlers (10) in adjacent air supply channels (8) are of opposite sense.
4. A combustion chamber according to claim 3, characterized in that the hydrogen supply hole (11) is arranged at an angle to the axial direction of the hydrogen supply channel (9), the hydrogen supply hole (11) being inclined to the axial direction of the combustion chamber, the angle of the hydrogen supply hole (11) axial direction to the hydrogen supply channel (9) axial direction being in the range of 30-60 degrees.
5. A combustion chamber according to any one of claims 1 to 4,
a plurality of cooling holes (12) are arranged on the outer wall of the cylinder body (2).
6. A combustion chamber according to any one of claims 1 to 4,
a plurality of mixing holes (13) are arranged at one end of the cylinder body (2) far away from the combustion chamber head section (1).
7. A gas turbine comprising a combustion chamber according to any one of claims 1-6.
8. A combustion control method for performing combustion using the combustion chamber according to any one of claims 1 to 6, comprising: after the fuel delivered to the cylinder body through the diffusion component burns stably, the fuel is delivered into the cylinder body through the nozzle component, so that the fuel burns.
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| CN202211075964.3A CN115325569B (en) | 2022-09-02 | 2022-09-02 | Combustion chamber, gas turbine and combustion control method |
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| CN202211075964.3A CN115325569B (en) | 2022-09-02 | 2022-09-02 | Combustion chamber, gas turbine and combustion control method |
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| CN115325569B true CN115325569B (en) | 2023-05-26 |
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|---|---|---|---|---|
| CN1403745A (en) * | 2001-08-24 | 2003-03-19 | 三菱重工业株式会社 | Gas turbine combustion chamber |
| CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
| CN105737200A (en) * | 2016-03-28 | 2016-07-06 | 中国科学院工程热物理研究所 | Atomizing nozzle, nozzle array and combustor |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH08210640A (en) * | 1995-02-03 | 1996-08-20 | Hitachi Ltd | Gas turbine burner |
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