CN116878027A - Gas turbine combustor nozzle structure and working method thereof - Google Patents
Gas turbine combustor nozzle structure and working method thereof Download PDFInfo
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- CN116878027A CN116878027A CN202310824174.9A CN202310824174A CN116878027A CN 116878027 A CN116878027 A CN 116878027A CN 202310824174 A CN202310824174 A CN 202310824174A CN 116878027 A CN116878027 A CN 116878027A
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- 238000000034 method Methods 0.000 title claims abstract description 23
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 404
- 239000003345 natural gas Substances 0.000 claims abstract description 202
- 239000001257 hydrogen Substances 0.000 claims abstract description 162
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 162
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 159
- 239000007789 gas Substances 0.000 claims abstract description 157
- 238000002485 combustion reaction Methods 0.000 claims abstract description 72
- 238000002156 mixing Methods 0.000 claims description 101
- 230000002093 peripheral effect Effects 0.000 claims description 30
- 238000009792 diffusion process Methods 0.000 claims description 24
- 230000008602 contraction Effects 0.000 claims description 14
- 230000000903 blocking effect Effects 0.000 claims description 7
- 230000000087 stabilizing effect Effects 0.000 claims description 7
- 230000009471 action Effects 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 description 15
- 230000009286 beneficial effect Effects 0.000 description 9
- 238000005496 tempering Methods 0.000 description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 7
- 229910052799 carbon Inorganic materials 0.000 description 7
- 239000000446 fuel Substances 0.000 description 7
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 150000002431 hydrogen Chemical class 0.000 description 5
- 230000000149 penetrating effect Effects 0.000 description 5
- 230000035515 penetration Effects 0.000 description 5
- 230000004323 axial length Effects 0.000 description 3
- 238000004891 communication Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 230000002349 favourable effect Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 239000003570 air Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Classifications
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention relates to the technical field of gas turbines, in particular to a gas turbine combustion chamber nozzle structure and a working method thereof. The gas turbine combustor nozzle structure includes: the first cylinder wall, the second cylinder wall, the third cylinder wall, the fourth cylinder wall and the fifth cylinder wall are coaxially arranged; the hydrogen flow path is formed between the second cylinder wall and the third cylinder wall at intervals; a second-stage natural gas flow path is formed between the third cylinder wall and the fourth cylinder wall at intervals; a second air flow path is formed between the fourth cylinder wall and the fifth cylinder wall at intervals; the first-stage step is arranged at the tail ends of the second-stage natural gas flow path and the second-stage air flow path; the second-stage step is arranged at the tail end of the hydrogen flow path; the first-stage step is provided with a natural gas high-speed jet hole and a second strip-shaped air supply hole; and the secondary step is provided with a hydrogen high-speed jet hole. The nozzle structure of the combustion chamber of the gas turbine can improve the flexibility of natural gas/hydrogen mixed combustion of the gas turbine.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine combustion chamber nozzle structure and a working method thereof.
Background
The gas turbine is used for ground power generation, often takes natural gas as fuel, releases a large amount of carbon dioxide during combustion, remarkably increases carbon emission, and under the restriction of environmental protection policy, energy conservation and emission reduction nowadays, the finding of a clean fuel to replace the traditional hydrocarbon fuel is a necessary path in the future. At present, natural gas and hydrogen are mixed for combustion in the existing gas turbine power plant, so that the effect of reducing carbon emission is achieved, the hydrogen mixing proportion of the future burner is gradually increased, and the carbon reduction effect is more remarkable.
In order to ensure stable combustion and safe combustion of the gas turbine, the natural gas/hydrogen is uniformly mixed, the existing gas turbine for hydrogen-doped combustion of the natural gas is required to be provided with a hydrogen mixing device outside the gas turbine body, namely the natural gas/hydrogen mixing device, and the natural gas and the hydrogen are uniformly mixed and then introduced into a nozzle of a combustion chamber of the gas turbine; when the hydrogen adding proportion is determined, the hydrogen adding proportion cannot be changed in the running process of the combustion engine, the real-time adjustment cannot be carried out, and the combustion engine can only run continuously with the current hydrogen adding proportion until the combustion engine is stopped.
Therefore, the existing gas turbine has lower flexibility of natural gas/hydrogen blending combustion, and is unfavorable for the normal operation of the gas turbine.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect of lower flexibility of natural gas/hydrogen blending combustion of the existing gas turbine in the prior art, so as to provide a gas turbine combustion chamber nozzle structure capable of improving the flexibility of natural gas/hydrogen blending combustion and a working method thereof.
In order to solve the technical problems, the present invention provides a nozzle structure of a combustion chamber of a gas turbine, comprising:
the first cylinder wall, the second cylinder wall, the third cylinder wall, the fourth cylinder wall and the fifth cylinder wall are coaxially arranged;
the hydrogen flow path is formed between the outer side peripheral wall of the second cylinder wall and the inner side peripheral wall of the third cylinder wall at radial intervals; a second-stage natural gas flow path is formed between the outer peripheral wall of the third cylinder wall and the inner peripheral wall of the fourth cylinder wall along the radial interval; a second-stage air flow path is formed between the outer peripheral wall of the fourth cylinder wall and the inner peripheral wall of the fifth cylinder wall along the radial interval;
the first-stage step is arranged at the tail ends of the second-stage natural gas flow path and the second-stage air flow path; the second-stage step is arranged at the tail end of the hydrogen flow path; one side of the first-stage step, which is axially close to the downstream, is enclosed with the outer peripheral wall of the fourth cylinder wall, and one side of the second-stage step, which is axially close to the downstream, is enclosed with the outer peripheral wall of the second cylinder wall and the inner peripheral wall of the fifth cylinder wall together to form a premixing zone;
the primary step is provided with a natural gas high-speed jet hole and a second strip-shaped air supply hole, the natural gas high-speed jet hole is suitable for communicating the secondary natural gas flow path with the premixing area, and the second strip-shaped air supply hole is suitable for communicating the secondary air flow path with the premixing area; the secondary step is provided with a hydrogen high-speed jet hole, and the hydrogen Gao Sushe jet hole is suitable for communicating the hydrogen flow path with the premixing area.
Optionally, the fifth cylinder wall includes a rectifying wall surface, and the rectifying wall surface includes a first contraction section and a second contraction section, where the first contraction section is located in a downstream area of the first stage step, and the second contraction section is located in a downstream area of the second stage step;
the radius of the first contraction section is r2, r2 is smaller than r1, wherein r1 is the radius of the primary step; the radius of the second contraction section is r4, r4 satisfies r4 < r3, wherein r3 is the radius of the secondary step, and r3 < r1.
Optionally, the first-stage step is further provided with a natural gas mixing hole, and the natural gas mixing hole is located at one side of the natural gas high-speed jet hole, which is far away from the third cylinder wall in the radial direction; one end of the natural gas blending hole is communicated with the secondary natural gas flow path, and the other end of the natural gas blending hole is communicated with the premixing zone;
the secondary step is also provided with a hydrogen mixing hole, and the hydrogen mixing hole is positioned at one side of the hydrogen high-speed jet hole, which is far away from the second cylinder wall along the radial direction; one end of the hydrogen blending hole is communicated with the hydrogen flow path, and the other end of the hydrogen blending hole is communicated with the premixing zone.
Optionally, an included angle between the central axis of the natural gas blending hole and/or the hydrogen blending hole and the central axis of the gas turbine combustion chamber nozzle structure is alpha, and alpha is more than or equal to 15 degrees and less than or equal to 60 degrees.
Optionally, a first air hole is formed in the second cylinder wall, and the distribution of the first air hole covers the premixing area, which is axially close to the downstream, of the secondary step;
and the fifth cylinder wall is provided with second air holes, and the second air holes are distributed to cover the premixing area of which the primary step is axially close to the downstream.
Optionally, the inner diameter of the first air hole and/or the second air hole is d, and d is more than or equal to 0.2mm and less than or equal to 1.0mm.
Optionally, the central axes of the natural gas high-speed jet hole and the hydrogen high-speed jet hole are parallel to the central axis of the gas turbine combustion chamber nozzle structure;
the natural gas high-speed jet hole and the hydrogen Gao Sushe jet hole are shrinkage holes, and the radial cross-sectional areas of the natural gas high-speed jet hole and the hydrogen high-speed jet hole are gradually reduced along the jet direction;
the shrinkage ratio of the natural gas high-speed jet hole and/or the hydrogen high-speed jet hole is gamma, and gamma satisfies gamma < 3.
Optionally, a primary air flow path is formed between the outer peripheral wall of the first cylinder wall and the inner peripheral wall of the second cylinder wall along a radial interval;
a cyclone is arranged at the outlet of the tail end of the primary air flow path, and the cyclone is suitable for enabling gas to generate cyclone;
The primary air flow path is provided with a steady flow part along the axial direction, which is close to one end of the cyclone, and the steady flow part is provided with a first strip-shaped air supply hole which is suitable for stabilizing the air flow.
Optionally, the inner side peripheral wall of the first cylinder wall encloses to form a first-stage natural gas flow path;
the tail end of the first cylinder wall is provided with a blocking part, the blocking part is provided with a natural gas jet hole, and the jet orifice of the natural gas jet hole is positioned between two adjacent blades of the cyclone.
The working method of the gas turbine combustion chamber nozzle structure provided by the invention is applied to the gas turbine combustion chamber nozzle structure, and the working method of the gas turbine combustion chamber nozzle structure comprises the following steps:
the method comprises the steps that a natural gas supply source supplies diffusion natural gas to a primary natural gas flow path, the diffusion natural gas is enabled to be injected into blade channels of a cyclone through a natural gas jet hole, meanwhile, a gas compressor supplies diffusion air to a primary air flow path, the diffusion air is enabled to be injected into the blade channels of the cyclone after being stabilized through a first strip-shaped air supply hole, the diffusion air is enabled to be quickly mixed with the diffusion natural gas and then is transmitted into a flame tube to be ignited by an igniter, and a diffusion combustion flame, namely, an on-duty flame is formed, and a stable backflow area is formed under the action of the cyclone to serve as a stable ignition source;
The method comprises the steps that premixed air is supplied to a secondary air flow path through a gas compressor, premixed natural gas is supplied to the secondary natural gas flow path through a natural gas supply source, so that a backflow area, namely a step vortex, is generated in a downstream area of a primary step after the premixed air is stabilized through a second strip-shaped air supply hole, the premixed natural gas is simultaneously discharged from a natural gas mixing hole and a natural gas high-speed jet hole and is rapidly mixed with air in the step vortex and flows downstream, and when the premixed air and the premixed natural gas flow to the secondary step, the step vortex is generated in the downstream area close to the secondary step;
the hydrogen is supplied to the hydrogen flow path by the hydrogen supply source, so that the hydrogen is transferred to the step vortex near the secondary step by the hydrogen mixing hole and the hydrogen high-speed jet hole, is quickly mixed with the premixed gas of the natural gas and the air, forms the premixed gas of the natural gas, the hydrogen and the air, propagates to the downstream of the nozzle, and is transmitted to the flame tube until being transferred to the flame tube, and is ignited and combusted by the duty flame.
The technical scheme of the invention has the following advantages:
1. according to the nozzle structure of the combustion chamber of the gas turbine, the first stage step and the second stage step are arranged to form the first sudden expansion structure and the second sudden expansion structure respectively, so that a backflow area is generated near the first stage step and the second stage step when gas flows through, namely, a step vortex is formed, the turbulence degree in the step vortex is high, natural gas and hydrogen are continuously mixed with air in the step vortex after being sent out from the step, and the three are quickly mixed uniformly and spread into a flame tube to be combusted in the downstream due to the fact that the internal turbulence degree is high and gas is refluxed; by arranging the natural gas high-speed jet hole and the hydrogen high-speed jet hole, the penetrability of natural gas and hydrogen is improved, the jet speed is high, surrounding gas can be attracted to gather to the jet beam based on Bernoulli effect, and rapid and uniform blending is facilitated. According to the gas turbine combustion chamber nozzle structure, through the arrangement, a hydrogen mixing device is not required to be built outside the gas turbine body, so that the natural gas, the hydrogen and the air can be quickly and uniformly mixed, the hydrogen mixing proportion can be adjusted in real time in the operation process of the gas turbine, the flexibility of natural gas/hydrogen mixing combustion of the gas turbine is improved, and in addition, the carbon emission can be remarkably reduced due to the fact that the natural gas is mixed with the hydrogen.
2. According to the gas turbine combustion chamber nozzle structure provided by the invention, the included angle alpha between the central axis of the natural gas mixing hole and/or the central axis of the hydrogen mixing hole and the central axis of the gas turbine combustion chamber nozzle structure is more than or equal to 15 degrees and less than or equal to 60 degrees, so that the mixing efficiency of gas can be improved, and the higher fluidity of gas can be ensured.
3. According to the gas turbine combustion chamber nozzle structure, the first air holes are formed in the second cylinder wall, so that the first air holes are densely distributed and cover the premixing zone, which is axially close to the downstream, of the secondary step; and the second air holes are formed in the fifth cylinder wall, so that the second air holes are densely distributed and cover the premixing area which is axially close to the downstream of the primary step, and therefore, the first air holes and the second air holes are used for jetting to form a gas film, and the direct contact of the combustible mixed gas and the wall surface is prevented, so that the flow speed of a mixed gas boundary layer is improved, the flow speed is higher than the flame propagation speed, the tempering of the boundary layer is prevented, the wall surface can be cooled, and the service life of the wall surface is prolonged.
4. According to the gas turbine combustion chamber nozzle structure provided by the invention, the natural gas high-speed jet holes are shrinkage holes, the radial cross-sectional areas of the natural gas high-speed jet holes are gradually reduced along the jet direction, the shrinkage ratio gamma of the natural gas high-speed jet holes meets gamma < 3, and the natural gas high-speed jet holes are beneficial to improving the jet speed and the penetration strength of the natural gas, so that the mixing effect can be enhanced on one hand, the overall average flow velocity of mixed gas can be improved on the other hand, and the tempering of the central flow is prevented; the flow holes of the hydrogen Gao Sushe are shrinkage holes, the radial cross-sectional areas of the flow holes are gradually reduced along the jet flow direction, the shrinkage ratio gamma of the high-speed jet holes of the hydrogen meets gamma < 3, the improvement of the jet flow speed and the penetration strength of the hydrogen is facilitated, the blending effect can be enhanced on one hand, the overall average flow velocity of the mixed gas can be improved on the other hand, and the tempering of the central flow is prevented.
5. According to the working method of the gas turbine combustion chamber nozzle structure, the step vortex is generated by arranging the steps, so that natural gas/hydrogen and air can be mixed uniformly, and therefore, the natural gas and the hydrogen can be independently supplied to the gas turbine combustion chamber, flow in the nozzle and are mixed, and the mixed gas is conveyed to the combustion chamber after being mixed uniformly. The method can enable the gas flow and the hydrogen flow to be independently regulated in the operation process of the gas engine, and the gas engine still keeps stable operation in the dynamic change of the fuel flow, so that the combustion flexibility of the gas engine is improved, and the safe and stable combustion of the gas engine is ensured; and the mixture of natural gas and hydrogen is combusted by the combustion engine, so that the carbon emission can be reduced, and the environmental protection effect is more remarkable along with the increase of the hydrogen loading proportion.
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 cross-sectional view of a gas turbine combustor nozzle configuration of the present invention;
FIG. 2 is an enlarged view of FIG. 1 at A;
FIG. 3 is a dimensional view of a first convergent section and a second convergent section of the gas turbine combustor nozzle structure in accordance with the invention;
FIG. 4 is a schematic isometric view of a gas turbine combustor nozzle configuration of the present invention;
FIG. 5 is a schematic elevational view of the nozzle configuration of the gas turbine combustor of the present invention;
FIG. 6 is a cross-sectional view of section B-B of FIG. 5;
FIG. 7 is a cross-sectional view of section C-C of FIG. 5;
FIG. 8 is an enlarged view of FIG. 6 at D;
FIG. 9 is a right side view of FIG. 5;
FIG. 10 is a schematic diagram of the operation of the nozzle configuration of the gas turbine combustor of the present invention to create a step vortex.
Reference numerals illustrate:
10. a first cylinder wall; 100. a primary natural gas flow path; 11. a blocking part; 110. natural gas jet holes;
20. a second cylinder wall; 200. a primary air flow path; 201. a first air hole; 21. a cyclone; 22. a steady flow part; 220. a first strip-shaped air supply hole;
30. a third cylinder wall; 300. a hydrogen flow path;
40. a fourth cylinder wall; 400. a secondary natural gas flow path;
50. a fifth cylinder wall; 500. a secondary air flow path; 501. a second air hole; 51. a rectifying wall surface; 511. a first constriction section; 512. a second constriction section;
60. A first step; 600. a premixing zone; 601. natural gas high velocity jet holes; 602. a natural gas blending orifice; 603. a second strip-shaped air supply hole;
70. a second step; 701. a hydrogen gas high-speed jet hole; 702. hydrogen blending holes.
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 apparatus or elements referred to must have a specific orientation, be constructed 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 can be understood by those of ordinary skill in the art according to the specific circumstances.
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.
Example 1
Referring to fig. 1 to 10, a gas turbine combustor nozzle structure according to the present embodiment includes:
a first cylinder wall 10, a second cylinder wall 20, a third cylinder wall 30, a fourth cylinder wall 40 and a fifth cylinder wall 50 which are coaxially arranged;
wherein, the outer peripheral wall of the second cylinder wall 20 and the inner peripheral wall of the third cylinder wall 30 form a hydrogen flow path 300 along the radial interval; a secondary natural gas flow path 400 is formed between the outer circumferential wall of the third cylinder wall 30 and the inner circumferential wall of the fourth cylinder wall 40 along a radial interval; a secondary air flow path 500 is formed between the outer circumferential wall of the fourth cylinder wall 40 and the inner circumferential wall of the fifth cylinder wall 50 along a radial direction;
A first stage step 60 provided at the ends of the second natural gas flow path 400 and the second air flow path 500; a secondary step 70 provided at the end of the hydrogen flow path 300; one side of the first step 60, which is axially adjacent to the downstream side, and the outer circumferential wall of the fourth cylinder wall 40, and one side of the second step 70, which is axially adjacent to the downstream side, and the outer circumferential wall of the second cylinder wall 20 and the inner circumferential wall of the fifth cylinder wall 50 are jointly enclosed to form a premixing zone 600;
the primary step 60 is provided with a natural gas high-speed jet hole 601 and a second strip-shaped air supply hole 603, the natural gas high-speed jet hole 601 is suitable for communicating the secondary natural gas flow path 400 with the premixing area 600, and the second strip-shaped air supply hole 603 is suitable for communicating the secondary air flow path 500 with the premixing area 600; the secondary step 70 is provided with a hydrogen high-speed jet hole 701, and the hydrogen Gao Sushe jet hole 701 is adapted to communicate the hydrogen flow path 300 with the premixing area 600.
The gas turbine combustion chamber nozzle structure is axially and sequentially divided into an air inlet section, a premixing section and a diffusion section, wherein the premixing section of the gas turbine combustion chamber nozzle structure is integrally contracted. Wherein the primary natural gas flow path 100, the primary air flow path 200, the hydrogen flow path 300, the secondary natural gas flow path 400 and the secondary air flow path 500 are positioned at the air inlet section of the nozzle structure of the combustion chamber of the gas turbine; the primary step 60, the rectifying wall surface 51, the secondary step 70, the first air hole 201, the second air hole 501, the natural gas high-speed jet hole 601, the natural gas blending hole 602, the second strip-shaped air supply hole 603, the hydrogen high-speed jet hole 701 and the hydrogen blending hole 702 are positioned at the premixing section of the nozzle structure of the combustion chamber of the gas turbine; the first strip air supply holes 220, swirlers 21 and natural gas jet holes 110 are located in the diffuser section of the gas turbine combustor nozzle structure.
It should be noted that, referring to fig. 1 and 4, the gas turbine combustor nozzle structure includes a first barrel wall 10, a second barrel wall 20, a third barrel wall 30, a fourth barrel wall 40 and a fifth barrel wall 50 coaxially disposed, and any two adjacent ones of the first barrel wall 10, the second barrel wall 20, the third barrel wall 30, the fourth barrel wall 40 and the fifth barrel wall 50 are disposed at radial intervals. Referring to fig. 1, a hydrogen flow path 300 is formed between the outer circumferential wall of the second cylinder wall 20 and the inner circumferential wall of the third cylinder wall 30 along a radial interval, a secondary natural gas flow path 400 is formed between the outer circumferential wall of the third cylinder wall 30 and the inner circumferential wall of the fourth cylinder wall 40 along a radial interval, and a secondary air flow path 500 is formed between the outer circumferential wall of the fourth cylinder wall 40 and the inner circumferential wall of the fifth cylinder wall 50 along a radial interval.
Note that, referring to fig. 1 and 2, the primary step 60 is disposed at the ends of the secondary natural gas flow path 400 and the secondary air flow path 500; one radial side of the primary step 60 is connected with the inner peripheral wall of the fifth cylinder wall 50, the other radial side is connected with the outer peripheral wall of the third cylinder wall 30, and one axial side of the primary step 60 is connected with the tail end of the fourth cylinder wall 40; the primary step 60 forms an included angle of 90 degrees with the central axis of the nozzle structure of the combustion chamber of the gas turbine so as to form a first sudden expansion structure, so that air flows through the first sudden expansion structure after being transmitted out, a backflow area, namely a step vortex, is generated in a downstream area adjacent to the primary step 60, the turbulence in the step vortex is high, and the reverse speed exists in the gas in the step vortex, so that the mixing of the air and the natural gas is facilitated, and the mixing efficiency of the gas is improved. The secondary step 70 is provided at the end of the hydrogen flow path 300; one radial side of the second step 70 is connected to the outer peripheral wall of the second cylinder wall 20, and the other radial side is connected to the end of the third cylinder wall 30; the second step 70 forms an included angle of 90 degrees with the central axis of the nozzle structure of the combustion chamber of the gas turbine, so as to form a second sudden expansion structure, thereby enabling air and natural gas to flow through the second sudden expansion structure, generating a backflow area, namely a step vortex, in a downstream area adjacent to the second step 70, wherein the turbulence in the step vortex is higher, and the gas inside the step vortex has a reverse speed, so that the mixing of the air, the natural gas and the hydrogen is facilitated, and the mixing efficiency of the gas is further improved. The side of the primary step 60 axially near the downstream is surrounded by the outer circumferential wall of the fourth cylinder wall 40, the side of the secondary step 70 axially near the downstream is surrounded by the outer circumferential wall of the second cylinder wall 20 and the inner circumferential wall of the fifth cylinder wall 50 together to form a premixing zone 600, and the premixing zone 600 is suitable for mixing natural gas, air and hydrogen.
Optionally, the number of the second strip-shaped air supply holes 603 is eight, and the eight second strip-shaped air supply holes 603 are uniformly arranged on the first stage step 60 along the circumferential direction, which is favorable for improving the uniformity of air jet flow, thereby improving the mixing uniformity and the mixing efficiency of air and natural gas.
It should be noted that, still referring to fig. 1 and fig. 2, the first stage step 60 is provided with a natural gas high-speed jet hole 601, so that one end of the natural gas high-speed jet hole 601 is communicated with the second stage natural gas flow path 400, and the other end is communicated with the premixing area 600, thereby improving the jet velocity and penetration strength of the natural gas, on one hand, enhancing the mixing effect of the natural gas and air, on the other hand, improving the overall average flow velocity of the mixed gas, and preventing the tempering of the central flow; the high-speed jet holes 701 for hydrogen are formed on the secondary step 70, so that one end of the flow holes 701 for hydrogen Gao Sushe is communicated with the hydrogen flow path 300, and the other end is communicated with the premixing area 600, thereby improving the jet speed and the penetrating strength of hydrogen, enhancing the mixing effect of natural gas, air and hydrogen on one hand, improving the overall average flow velocity of mixed gas, and preventing the tempering of the central flow on the other hand.
In this embodiment, the first step 60 and the second step 70 are provided to form the first sudden expansion structure and the second sudden expansion structure respectively, so that when the gas flows through, a backflow area, namely a step vortex, is generated near the first step 60 and the second step 70, the turbulence in the step vortex is higher, the natural gas and the hydrogen are continuously mixed with air in the step vortex after being sent out from the step, and due to the higher internal turbulence, and the gas backflow, the three are quickly mixed uniformly and spread to the flame tube downstream for combustion; by arranging the natural gas high-speed jet hole 601 and the hydrogen high-speed jet hole 701, the penetrability of natural gas and hydrogen is improved, and the jet speed is high, so that surrounding gas can be attracted to gather to the jet beam based on Bernoulli effect, and quick and uniform mixing is facilitated. According to the gas turbine combustion chamber nozzle structure, through the arrangement, a hydrogen mixing device is not required to be built outside the gas turbine body, so that the natural gas, the hydrogen and the air can be quickly and uniformly mixed, the hydrogen mixing proportion can be adjusted in real time in the operation process of the gas turbine, the flexibility of natural gas/hydrogen mixing combustion of the gas turbine is improved, and in addition, the carbon emission can be remarkably reduced due to the fact that the natural gas is mixed with the hydrogen.
Specifically, the fifth cylinder wall 50 includes a rectifying wall 51, and the rectifying wall 51 includes a first contraction section 511 and a second contraction section 512, where the first contraction section 511 is located in a downstream area of the first stage step 60, and the second contraction section 512 is located in a downstream area of the second stage step 70;
the radius of the first convergent section 511 is r2, r2 satisfies r2 < r1, where r1 is the radius of the primary step 60; the radius of the second convergent section 512 is r4, r4 satisfying r4 < r3, where r3 is the radius of the secondary step 70, and r3 < r1.
Specifically, the primary step 60 is further provided with a natural gas blending hole 602, and the natural gas blending hole 602 is located at a side of the natural gas high-speed jet hole 601 away from the third cylinder wall 30 in the radial direction; one end of the natural gas blending bore 602 is in communication with the secondary natural gas flowpath 400 and the other end is in communication with the premixing zone 600;
the secondary step 70 is further provided with a hydrogen blending hole 702, and the hydrogen blending hole 702 is located at one side of the hydrogen Gao Sushe flow hole 701 away from the second cylinder wall 20 in the radial direction; the hydrogen blending hole 702 has one end communicating with the hydrogen flow path 300 and the other end communicating with the premixing zone 600.
Note that, referring to fig. 3, the rectifying wall 51 is disposed on the fifth cylinder wall 50 in a convergent manner along the airflow direction, and the rectifying wall 51 includes a first convergent section 511 and a second convergent section 512. The first constriction 511 is located in the downstream area of the first stage 60, the radius r2 of the first constriction 511 is smaller than the radius r1 of the first stage 60, when the premixed air is delivered from the second strip-shaped air supply hole 603 and rapidly diffuses, part of the premixed air flows near the first stage 60 to generate a step vortex, the rest part of the premixed air flows downstream of the nozzle and collides with the first constriction 511 when flowing to the rectifying wall surface corresponding to the first constriction 511, so that the part of the premixed air generates more obvious component speed along the radial inward direction of the nozzle, and the natural gas delivered from the natural gas mixing hole 602 has component speed along the radial outward direction of the nozzle, and the radial speeds of the two are opposite, but the axial speeds are the same, thereby being beneficial to rapid mixing of air and natural gas; otherwise, if the radius r2 of the first constriction 511 is greater than the radius r1 of the primary step 60, the premixed air passing out of the second strip-shaped air supply hole 603 does not collide with the rectifying wall surface corresponding to the first constriction 511, or even if there is a collision, the portion of premixed air does not generate a significant velocity of the portion radially inward of the nozzle. Similarly, the second constriction 512 is located in the downstream area of the second stage 70, the radius r4 of the second constriction 512 is smaller than the radius r3 of the second stage 70, and when the mixed gas of air and natural gas moves towards the end of the nozzle, part of the mixed gas flows to the vicinity of the second stage 70 to generate a stage vortex, and the rest flows towards the downstream of the nozzle, and collides with the second constriction 512 when flowing to the rectifying wall surface corresponding to the second constriction 512, so that the part of the mixed gas generates more remarkable component speed along the radial inward direction of the nozzle, and the hydrogen delivered from the hydrogen blending hole 702 has component speed along the radial outward direction of the nozzle, and the radial speeds of the two component speeds are opposite, but the axial speeds are the same, thereby being beneficial to rapid blending of air and natural gas with hydrogen.
It should be noted that, as shown in fig. 1, the hydrogen diffusion speed is faster and the required premixing distance is shorter, so in this embodiment, the axial length of the hydrogen flow path 300 is greater than the axial length of the secondary natural gas flow path 400, that is, the premixing length of hydrogen is smaller than the premixing length of natural gas.
Optionally, the curved portions of the inner and outer sides of the rectifying wall 51 are rounded to reduce the gas flow loss.
Specifically, the angle between the central axis of the natural gas blending bore 602 and/or the hydrogen blending bore 702 and the central axis of the gas turbine combustor nozzle structure is α, which satisfies 15+.ltoreq.α.ltoreq.60 °.
It should be noted that, referring to fig. 2, the central axis of the gas turbine combustor nozzle structure refers to the axis indicated by the lead line "L" in fig. 1-3, wherein the central axis L of the gas turbine combustor nozzle structure at two included angles shown in fig. 2 can be obtained according to the parallel principle, and will not be described herein again; the central axis of the natural gas blending bore 602 refers to the axis indicated by the lead "P" in fig. 2, the central axis of the hydrogen blending bore 702 refers to the axis indicated by the lead "Q" in fig. 2, and the angle between the central axis of the natural gas blending bore 602 and/or the hydrogen blending bore 702 and the central axis of the gas turbine combustor nozzle structure refers to the angle "α" in fig. 2. The included angle α cannot be too small, or the jet flow of the natural gas blending hole 602 and/or the hydrogen blending hole 702 is easily caused to have too small radial component speed, and too large axial component speed, which is unfavorable for blending, and the jet flow penetrability is low, which is also unfavorable for blending, so that the included angle α needs to satisfy α be equal to or greater than 15 °; the included angle α should not be too large, otherwise it would be easy to cause too large a radial velocity of the jet of the natural gas blending hole 602 and/or the hydrogen blending hole 702, and too small a radial velocity of the jet, and the larger radial velocity would slow down another fluid blended therewith, which is not beneficial to flow, and is also not beneficial to blending, so the included angle α needs to satisfy α being less than or equal to 60 °; the included angle alpha between the central axis of the natural gas blending hole 602 and/or the hydrogen blending hole 702 and the central axis of the nozzle structure of the combustion chamber of the gas turbine meets the requirement that alpha is less than or equal to 15 degrees and less than or equal to 60 degrees, so that the blending efficiency of the gas can be improved, and the higher fluidity of the gas can be ensured.
Optionally, the included angle α between the central axis of the natural gas blending hole 602 and the central axis of the nozzle structure of the combustion chamber of the gas turbine is α=30°, so that the natural gas is obliquely injected into the air flow, which is beneficial to uniform blending; the included angle α between the central axis of the hydrogen blending hole 702 and the central axis of the nozzle structure of the combustion chamber of the gas turbine is α=30°, so that the hydrogen is obliquely injected into the mixed gas of the natural gas and the air, which is beneficial to blending uniformity.
Specifically, the second cylinder wall 20 is provided with first air holes 201, and the distribution of the first air holes 201 covers the premixing area 600 axially near the downstream of the secondary step 70;
the fifth cylinder wall 50 is provided with second air holes 501, and the second air holes 501 are distributed to cover the premixing area 600 axially near the downstream of the primary step 60.
It should be noted that, referring to fig. 1, the second cylinder wall 20 and the fifth cylinder wall 50 are wall surfaces contacted when the natural gas, the hydrogen gas and the air flow in a premixing manner, and the first air holes 201 are formed in the second cylinder wall 20, so that the first air holes 201 are densely distributed to cover the premixing area 600 of the second step 70 axially near the downstream; and by forming the second air holes 501 on the fifth cylinder wall 50, the second air holes 501 are densely distributed and cover the premixing area 600 near the downstream of the primary step 60 along the axial direction, so that the air film is formed by the jet flow of the first air holes 201 and the second air holes 501, and the direct contact of the combustible mixed gas and the wall surface is prevented, thereby improving the flow speed of the mixed gas boundary layer, making the flow speed greater than the flame propagation speed, preventing the boundary layer from tempering, simultaneously cooling the wall surface and prolonging the service life of the wall surface. Meanwhile, the premixing section of the nozzle structure of the combustion chamber of the gas turbine is integrally in a contracted shape, and the natural gas high-speed jet holes 601 and the hydrogen high-speed jet holes 701 are all contraction holes, so that the average flow speed of mixed gas can be obviously improved, the average flow speed is higher than the flame propagation speed, and the backfire of the central flow is prevented.
Specifically, the inner diameter of the first air hole 201 and/or the second air hole 501 is d, and d is 0.2 mm.ltoreq.d.ltoreq.1.0 mm.
It should be noted that, the inner diameter d (not shown) of the first air hole 201 and/or the second air hole 501 is not too small, otherwise, the air flow area is too small, and the air flow is limited, so that the inner diameter d needs to satisfy d being greater than or equal to 0.2mm; the inner diameter d cannot be too large, otherwise, the air jet speed is easy to reduce, the penetrating power is weakened, and the mixing is not facilitated, so that the inner diameter d is required to meet d less than or equal to 1.0mm; in summary, the inner diameter d of the first air hole 201 and/or the second air hole 501 satisfies 0.2mm less than or equal to d less than or equal to 1.0mm, so that the air jet velocity is ensured to be at a faster level, the penetrating power of the jet and the average flow velocity of the mixed air are enhanced, and sufficient air flow is ensured, thereby improving the mixing efficiency.
Specifically, the central axes of the natural gas high-speed orifice 601 and the hydrogen Gao Sushe orifice 701 are parallel to the central axis of the gas turbine combustor nozzle structure;
the natural gas high-speed jet hole 601 and the hydrogen Gao Sushe jet hole 701 are shrink holes, and the radial cross-sectional areas of the natural gas high-speed jet hole 601 and the hydrogen Gao Sushe jet hole 701 are gradually reduced along the jet direction;
The contraction ratio of the natural gas high-speed orifice 601 and/or the hydrogen Gao Sushe orifice 701 is gamma, and gamma satisfies gamma < 3.
It should be noted that, referring to fig. 2, the central axis of the natural gas high-speed jet hole 601 is parallel to the central axis of the nozzle structure of the combustion chamber of the gas turbine, the radial cross-sectional area of the natural gas high-speed jet hole 601 is a shrinkage hole, and gradually decreases along the jet direction, the shrinkage ratio γ of the natural gas high-speed jet hole 601 satisfies γ < 3, which is favorable for improving the jet speed and the penetration strength of the natural gas, on one hand, the blending effect can be enhanced, on the other hand, the overall average flow velocity of the mixed gas can be improved, and the backfire of the central flow is prevented; similarly, the central axis of the hydrogen Gao Sushe flow hole 701 is parallel to the central axis of the nozzle structure of the combustion chamber of the gas turbine, the hydrogen Gao Sushe flow hole 701 is a shrinkage hole, the radial cross-sectional area of the shrinkage hole is gradually reduced along the jet direction, the shrinkage ratio gamma of the hydrogen Gao Sushe flow hole 701 satisfies gamma < 3, which is favorable for improving the jet speed and the penetration strength of hydrogen, on one hand, the mixing effect can be enhanced, on the other hand, the overall average flow velocity of mixed gas can be improved, and the tempering of the central flow is prevented.
Compared with the existing in-service gas turbine combustor nozzle, the premixing section has no swirl component, so that the premixing section has a compact and concise overall structure, remarkably reduces the production and processing costs, and is more beneficial to maintenance and replacement.
Specifically, a primary air flow path 200 is formed between the outer circumferential wall of the first cylinder wall 10 and the inner circumferential wall of the second cylinder wall 20 at a radial interval;
a cyclone 21 is arranged at the outlet of the tail end of the primary air flow path 200, and the cyclone 21 is suitable for generating cyclone flow for gas;
the primary air flow path 200 is provided with a flow stabilizing portion 22 along an axial direction near one end of the cyclone 21, the flow stabilizing portion 22 is provided with a first strip-shaped air supply hole 220, and the first strip-shaped air supply hole 220 is suitable for stabilizing air flow.
It should be noted that, referring to fig. 1, the end face of the end of the primary air flow path 200 is chamfered, so that the fresh premixed air is facilitated to flow to the recirculation zone formed downstream of the cyclone 21, and is convenient to be ignited and burned by the duty flame.
Alternatively, the number of the first strip-shaped air supply holes 220 is four, and four of the first strip-shaped air supply holes 220 are uniformly provided around the circumference of the flow stabilizing part 22, thereby stabilizing the air flow.
Specifically, the inner peripheral wall of the first cylinder wall 10 encloses a primary natural gas flow path 100;
the tail end of the first cylinder wall 10 is provided with a blocking part 11, the blocking part 11 is provided with a natural gas jet hole 110, and the jet orifice of the natural gas jet hole 110 is positioned between two adjacent blades of the cyclone 21.
Example two
Unlike the first embodiment, in this embodiment, by making the axial length of the hydrogen flow path 300 equal to that of the secondary natural gas flow path 400, that is, only providing a first step, a single sudden expansion structure is formed, so as to form a step vortex, and the rectifying wall surface also corresponds to only one constriction section, the nozzle structure can be simplified on the basis of not affecting the blending effect, and the nozzle structure is more compact.
Example III
The working method of the gas turbine combustor nozzle structure provided by the embodiment is applied to the gas turbine combustor nozzle structure, and the working method of the gas turbine combustor nozzle structure comprises the following steps:
the natural gas supply source supplies the diffusion natural gas to the primary natural gas flow path 100, so that the diffusion natural gas is injected into the blade channels of the cyclone 21 through the natural gas jet holes 110, meanwhile, the gas compressor supplies the diffusion air to the primary air flow path 200, so that the diffusion air is injected into the blade channels of the cyclone 21 after being stabilized through the first strip-shaped air supply holes 220, is quickly mixed with the diffusion natural gas, is then transferred into the flame tube and is ignited by the igniter, and forms diffusion combustion flame, namely duty flame, and forms a stable backflow area under the action of the cyclone 21 to serve as a stable ignition source;
The premixed air is supplied to the secondary air flow path 500 by the compressor, the premixed natural gas is supplied to the secondary natural gas flow path 400 by the natural gas supply source, so that a backflow area, namely a step vortex, is generated in a downstream area of the primary step 60 after the premixed air is stabilized by the second strip-shaped air supply hole 603, and meanwhile, the premixed natural gas is conveyed out of the natural gas mixing hole 602 and the natural gas high-speed jet hole 601, is rapidly mixed with air in the step vortex and flows downstream, and when the premixed air and the premixed natural gas flow to the secondary step 70, the step vortex is generated in the downstream area of the immediately adjacent secondary step 70;
hydrogen is supplied to the hydrogen flow path 300 from a hydrogen supply source, so that the hydrogen is transferred from the hydrogen blending hole 702 and the hydrogen high-speed jet hole 701 into the step vortex near the secondary step 70, is quickly blended with the premixed gas of natural gas and air, forms the premixed gas of the natural gas, the hydrogen and the air, propagates to the downstream of the nozzle, and is transmitted to the flame tube until being transferred to the flame tube, and is ignited and combusted by the duty flame.
It should be noted that, in the present invention, the fuel used in the middle shift combustion, i.e. the diffusion combustion, is natural gas, but not hydrogen or the mixture of natural gas and hydrogen, because the diffusion combustion is different from the premixed combustion, the flame surface temperature cannot be adjusted, if the fuel contains hydrogen, the flame surface temperature will be significantly increased, and the emission of thermal nitrogen oxides will be significantly increased, so when pure natural gas is used, the flame surface temperature can be kept at a lower level, and the generation of thermal nitrogen oxides can be effectively controlled.
The working method of the gas turbine combustor nozzle structure of the invention is described in detail below:
when the gas turbine combustor nozzle structure works, the diffused natural gas is injected between the blade channels of the cyclone 21 through the natural gas jet holes 110, meanwhile, the diffused air is injected between the blade channels of the cyclone 21 after being stabilized through the first strip-shaped air supply holes 220, is quickly mixed with the diffused natural gas, is then transmitted into the flame tube and is ignited by the igniter, so that a diffusion combustion flame, namely an on-duty flame, is formed, and forms a stable backflow area under the action of the cyclone 21 to serve as a stable ignition source. Meanwhile, the premixed air is ejected after being stabilized by the second strip-shaped air supply hole 603, and because of the existence of the first step 60, the air flows through the sudden expansion structure after being outgoing, a backflow area, namely a step vortex, is generated in a downstream area close to the first step 60, as shown in fig. 10, the turbulence in the step vortex is higher, and the reverse speed exists in the gas in the step vortex; meanwhile, the premixed natural gas is delivered from the natural gas mixing hole 602 and the natural gas high-speed jet hole 601, is quickly mixed with air in the step vortex and flows downwards, the high turbulence degree and the reverse speed in the step vortex are beneficial to gas mixing, and as the included angle between the central axis of the natural gas mixing hole 602 and the central axis of the nozzle structure of the combustion chamber of the gas turbine is alpha, the natural gas is obliquely injected into the air flow, so that uniform mixing is facilitated, the central axis of the natural gas high-speed jet hole 601 is parallel to the central axis of the nozzle structure of the combustion chamber of the gas turbine, the natural gas high-speed jet hole 601 is a shrinkage hole, the natural gas jet speed and the penetrating strength are facilitated to be improved, on one hand, the mixing effect can be enhanced, on the other hand, the overall average flow speed of the mixed gas can be improved, and the tempering of the central flow is prevented. When flowing to the secondary step 70, similar to the above, step vortex is generated in the downstream area of the immediately downstream step 70, meanwhile, hydrogen is transferred from the hydrogen mixing hole 702 and the hydrogen high-speed jet hole 701 to the step vortex near the secondary step 70, and is quickly mixed with the pre-mixed gas of the natural gas and the air to form the pre-mixed gas of the natural gas, the hydrogen and the air, and the pre-mixed gas is transferred to the downstream of the nozzle until the pre-mixed gas is transferred to the flame tube, and is ignited and combusted by the duty flame; the included angle between the central axis of the hydrogen blending hole 702 and the central axis of the nozzle structure of the combustion chamber of the gas turbine is alpha, so that hydrogen can be obliquely injected into the mixed gas of natural gas and air, the mixing uniformity is facilitated, the central axis of the hydrogen high-speed jet hole 701 is parallel to the central axis of the nozzle structure of the combustion chamber of the gas turbine, the hydrogen high-speed jet hole 701 is a shrinkage hole, the jet speed and the penetrating strength of the hydrogen are facilitated to be improved, the mixing effect can be enhanced on one hand, the overall average flow velocity of the mixed gas can be improved on the other hand, and the tempering of the central flow is prevented.
It should be noted that, the natural gas hydrogen-adding combustion scheme adopted by the gas engine before improvement needs to complete the mixing work before the natural gas and the hydrogen are conveyed to the combustion chamber, and once the hydrogen adding proportion is determined, the gas engine cannot be changed in the operation process, only the current hydrogen adding amount can be kept to operate, otherwise, when the hydrogen adding amount changes due to some reasons and the natural gas flow is unchanged, the combustion of the gas engine is unstable and even the gas engine jumps easily. According to the working method of the gas turbine combustion chamber nozzle structure, the step vortex is generated by arranging the steps, so that natural gas/hydrogen and air can be mixed uniformly rapidly, and therefore, the natural gas and the hydrogen can be independently supplied to the gas turbine combustion chamber, flow in the nozzle and are mixed, and the mixed gas is conveyed to the combustion chamber after being mixed uniformly. The method can enable the gas flow and the hydrogen flow to be independently regulated in the operation process of the gas engine, and the gas engine still keeps stable operation in the dynamic change of the fuel flow, so that the combustion flexibility of the gas engine is improved, and the safe and stable combustion of the gas engine is ensured; and the mixture of natural gas and hydrogen is combusted by the combustion engine, so that the carbon emission can be reduced, and the environmental protection effect is more remarkable along with the increase of the hydrogen loading proportion.
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. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (10)
1. A gas turbine combustor nozzle structure comprising:
the first cylinder wall (10), the second cylinder wall (20), the third cylinder wall (30), the fourth cylinder wall (40) and the fifth cylinder wall (50) are coaxially arranged;
wherein a hydrogen flow path (300) is formed between the outer peripheral wall of the second cylinder wall (20) and the inner peripheral wall of the third cylinder wall (30) along the radial interval; a second-stage natural gas flow path (400) is formed between the outer peripheral wall of the third cylinder wall (30) and the inner peripheral wall of the fourth cylinder wall (40) along the radial interval; a secondary air flow path (500) is formed between the outer peripheral wall of the fourth cylinder wall (40) and the inner peripheral wall of the fifth cylinder wall (50) along the radial interval;
a primary step (60) provided at the ends of the secondary natural gas flow path (400) and the secondary air flow path (500); a secondary step (70) provided at the end of the hydrogen flow path (300); one side of the primary step (60) close to the downstream in the axial direction is enclosed with the outer peripheral wall of the fourth cylinder wall (40) and one side of the secondary step (70) close to the downstream in the axial direction is enclosed with the outer peripheral wall of the second cylinder wall (20) and the inner peripheral wall of the fifth cylinder wall (50) together to form a premixing zone (600);
The primary step (60) is provided with a natural gas high-speed jet hole (601) and a second strip-shaped air supply hole (603), the natural gas high-speed jet hole (601) is suitable for communicating the secondary natural gas flow path (400) with the premixing area (600), and the second strip-shaped air supply hole (603) is suitable for communicating the secondary air flow path (500) with the premixing area (600); the secondary step (70) is provided with a hydrogen high-speed jet hole (701), and the hydrogen Gao Sushe jet hole (701) is suitable for communicating the hydrogen flow path (300) with the premixing area (600).
2. The gas turbine combustor nozzle structure of claim 1, wherein the fifth cartridge wall (50) comprises a rectifying wall (51), the rectifying wall (51) comprising a first converging section (511) and a second converging section (512), the first converging section (511) being located in a downstream region of the primary step (60), the second converging section (512) being located in a downstream region of the secondary step (70);
the radius of the first contraction section (511) is r 2 ，r 2 Satisfy r 2 ＜r 1 Wherein r is 1 Radius for the primary step (60); the radius of the second contraction section (512) is r 4 ，r 4 Satisfy r 4 ＜r 3 Wherein r is 3 Is the radius of the secondary step (70), r 3 ＜r 1 。
3. The gas turbine combustor nozzle structure of claim 1, wherein the primary step (60) is further provided with a natural gas blending hole (602), and the natural gas blending hole (602) is located at a side of the natural gas high-speed jet hole (601) radially away from the third cylinder wall (30); one end of the natural gas blending hole (602) is communicated with the secondary natural gas flow path (400), and the other end is communicated with the premixing zone (600);
the secondary step (70) is also provided with a hydrogen mixing hole (702), and the hydrogen mixing hole (702) is positioned at one side of the hydrogen Gao Sushe flow hole (701) away from the second cylinder wall (20) along the radial direction; one end of the hydrogen blending hole (702) is communicated with the hydrogen flow path (300), and the other end is communicated with the premixing zone (600).
4. A gas turbine combustor nozzle structure according to claim 3, characterized in that the angle between the central axis of the natural gas blending bore (602) and/or the hydrogen blending bore (702) and the central axis of the gas turbine combustor nozzle structure is α, α satisfying 15 ° - α -60 °.
5. The gas turbine combustor nozzle structure of claim 1, wherein the second cylinder wall (20) is provided with first air holes (201), and the distribution of the first air holes (201) covers a premixing zone (600) axially close to the downstream of the secondary step (70);
And a second air hole (501) is formed in the fifth cylinder wall (50), and the second air holes (501) are distributed to cover the premixing zone (600) which is axially close to the downstream of the primary step (60).
6. The gas turbine combustor nozzle structure of claim 5, wherein the first air holes (201) and/or the second air holes (501) have an inner diameter d, d satisfying 0.2mm +.d +.1.0 mm.
7. The gas turbine combustor nozzle structure of claim 1, wherein the central axes of the natural gas high velocity orifice (601) and the hydrogen Gao Sushe orifice (701) are both parallel to the central axis of the gas turbine combustor nozzle structure;
the natural gas high-speed jet hole (601) and the hydrogen Gao Sushe jet hole (701) are shrinkage holes, and the radial cross-sectional areas of the natural gas high-speed jet hole (601) and the hydrogen Gao Sushe jet hole (701) are gradually reduced along the jet direction;
the shrinkage ratio of the natural gas high-speed jet hole (601) and/or the hydrogen Gao Sushe jet hole (701) is gamma, and gamma satisfies gamma < 3.
8. The gas turbine combustor nozzle structure of any one of claims 1-7, wherein a primary air flow path (200) is formed between an outer peripheral wall of the first cartridge wall (10) and an inner peripheral wall of the second cartridge wall (20) along a radial interval;
A cyclone (21) is arranged at the outlet of the tail end of the primary air flow path (200), and the cyclone (21) is suitable for generating cyclone flow for gas;
one end of the primary air flow path (200) which is axially close to the cyclone (21) is provided with a steady flow part (22), the steady flow part (22) is provided with a first strip-shaped air supply hole (220), and the first strip-shaped air supply hole (220) is suitable for stabilizing air flow.
9. The gas turbine combustor nozzle structure of claim 8, wherein an inner peripheral wall of the first cartridge wall (10) encloses a primary natural gas flow path (100);
the tail end of the first cylinder wall (10) is provided with a blocking part (11), the blocking part (11) is provided with a natural gas jet hole (110), and the jet orifice of the natural gas jet hole (110) is positioned between two adjacent blades of the cyclone (21).
10. A method of operating a gas turbine combustor nozzle configuration as defined in any one of claims 1 to 9, comprising:
the natural gas supply source supplies the diffusion natural gas to the primary natural gas flow path (100), so that the diffusion natural gas is injected between blade channels of the cyclone (21) through the natural gas injection holes (110), meanwhile, the gas compressor supplies the diffusion air to the primary air flow path (200), so that the diffusion air is injected between the blade channels of the cyclone (21) after being stabilized through the first strip-shaped air supply holes (220), is quickly mixed with the diffusion natural gas, is then delivered into the flame tube and is ignited by the igniter, a diffusion combustion flame, namely an on-duty flame, is formed, and is used as a stable ignition source under the action of the cyclone (21);
The premixed air is supplied to the secondary air flow path (500) by the air compressor, the premixed natural gas is supplied to the secondary natural gas flow path (400) by the natural gas supply source, so that a backflow area, namely a step vortex, is generated in a downstream area of the primary step (60) after the premixed air is stabilized by the second strip-shaped air supply hole (603), and meanwhile, the premixed natural gas is conveyed out of the natural gas mixing hole (602) and the natural gas high-speed jet hole (601) and is quickly mixed with air in the step vortex and flows downstream, and when the premixed air and the premixed natural gas flow to the secondary step (70), the step vortex is generated in the downstream area which is close to the secondary step (70);
the hydrogen is supplied to the hydrogen flow path (300) by the hydrogen supply source, so that the hydrogen is transferred into the step vortex near the secondary step (70) by the hydrogen blending hole (702) and the hydrogen high-speed jet hole (701), is quickly blended with the premixed gas of the natural gas and the air, forms the premixed gas of the natural gas, the hydrogen and the air, propagates to the downstream of the nozzle, is transferred to the flame tube, and is ignited and combusted by the duty flame.
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| CN202310824174.9A CN116878027A (en) | 2023-07-06 | 2023-07-06 | Gas turbine combustor nozzle structure and working method thereof |
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| CN202310824174.9A CN116878027A (en) | 2023-07-06 | 2023-07-06 | Gas turbine combustor nozzle structure and working method thereof |
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