CN117053230A - Dual-fuel low-emission gas turbine combustion chamber with air conditioning system - Google Patents
Dual-fuel low-emission gas turbine combustion chamber with air conditioning system Download PDFInfo
- Publication number
- CN117053230A CN117053230A CN202310915577.4A CN202310915577A CN117053230A CN 117053230 A CN117053230 A CN 117053230A CN 202310915577 A CN202310915577 A CN 202310915577A CN 117053230 A CN117053230 A CN 117053230A
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- China
- Prior art keywords
- combustion chamber
- air
- flame tube
- baffle
- throttle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 97
- 239000000446 fuel Substances 0.000 title claims abstract description 67
- 238000004378 air conditioning Methods 0.000 title claims abstract description 14
- 230000001105 regulatory effect Effects 0.000 claims abstract description 21
- 238000002156 mixing Methods 0.000 claims abstract description 14
- 239000011229 interlayer Substances 0.000 claims abstract description 5
- 230000009977 dual effect Effects 0.000 claims description 9
- 239000007788 liquid Substances 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 24
- 239000002737 fuel gas Substances 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
-
- 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
-
- 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
-
- 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
- F23R3/36—Supply of different fuels
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides a dual-fuel low-emission gas turbine combustion chamber with an air conditioning system, which comprises a bleed air channel, a throttle baffle, a combustion chamber shell, a dual-fuel nozzle and a flame tube, wherein the bleed air channel is arranged on the throttle baffle; the bleed air channel is arranged outside the combustion chamber housing; the throttle baffle, the dual-fuel nozzle and the flame tube are arranged on the inner side of the shell of the combustion chamber; the throttle baffle is arranged in an interlayer between the flame tube and the combustion chamber shell; the fuel outlet of the dual-fuel nozzle is connected with the flame tube; the flame tube is connected with the outlet of the combustion chamber. The invention can be applied to the combustion chamber of the invention, in the whole operation process of the gas turbine, according to the characteristics of different phase fuels, the distribution of the air inflow, the main fuel air amount and the blending air amount of the nozzle in the combustion chamber can be regulated on line, so that the high-quality compatible gas fuel and liquid fuel of the gas turbine can be realized, and meanwhile, the processing precision tolerance of the combustion chamber of the invention to the flow area of the nozzle and the flame tube is high, and the invention has lower processing and debugging cost and shorter period.
Description
Technical Field
The invention belongs to the field of heat energy and power engineering, and particularly relates to a dual-fuel low-emission gas turbine combustion chamber with an air conditioning system.
Background
With the continuous optimization of energy configuration, the social requirements for fuel compatibility and emission environmental protection of the power equipment gas turbine are continuously improved. The dual fuel low emission combustor is a core component of a gas turbine for achieving multiple fuel combustion and is also one of key components for reducing emission. In the working process of the combustion chamber of the dual-fuel low-emission gas turbine, the required air distribution modes of the combustion chamber are different due to the difference of different phase fuel characteristics: when using gas fuel, insufficient combustion premix air entering from the front end of the flame tube will cause the temperature of the combustion zone to be too high, thereby generating a large amount of pollutants NOx; when liquid fuel is used, the evaporation combustion speed of the liquid fuel is slower, so that too much air entering from the front end of the flame tube can cause the liquid fuel to be blown to the downstream of the flame tube too early to be combusted completely, and meanwhile, the main combustion air and the blending air are insufficient in the uniformity of the outlet temperature of the combustion chamber, so that the service life of turbine blades at the downstream of the combustion chamber is influenced. Thus, reasonable air distribution is one of the key technologies for the combustion chamber to accommodate multiple phase fuels and achieve low emission combustion of the gaseous fuels.
Disclosure of Invention
The invention aims to provide a dual-fuel low-emission gas turbine combustion chamber with an air conditioning system, which can be applied to combustion chambers such as a dual-fuel gas turbine combustion chamber and the like needing air distribution and adjustment, realizes on-line adjustment of air inflow of a nozzle in the combustion chamber, main combustion air quantity and blending air quantity distribution, and is suitable for switching different phase fuels of a gas turbine. .
A dual fuel low emission gas turbine combustor with an air conditioning system includes a bleed air passage, a throttle baffle, a combustor casing, a dual fuel nozzle, and a combustor basket; the bleed air channel is arranged outside the combustion chamber housing; the throttle baffle, the dual-fuel nozzle and the flame tube are arranged on the inner side of the shell of the combustion chamber; the throttle baffle is arranged in an interlayer between the flame tube and the combustion chamber shell; the fuel outlet of the dual-fuel nozzle is connected with the flame tube; the flame tube is connected with the outlet of the combustion chamber.
Further, the bleed air channel comprises a bleed air channel pipeline and a bleed air flow regulating valve; the air-entraining channel pipeline is welded on the combustion chamber shell, one end of the air-entraining channel pipeline is close to the air inlet of the combustion chamber, the other end of the air-entraining channel pipeline is far away from the air inlet of the combustion chamber and is positioned on the other side of the throttle baffle, and the air-entraining channel pipeline is provided with an air-entraining flow regulating valve for regulating the air flow in the air-entraining channel pipeline.
Further, the wall surface of the flame tube is provided with a flame tube main combustion hole and a flame tube mixing hole; and a baffle groove is formed in the outer side of the flame tube and is used for installing and fixing a throttling baffle.
Further, the throttle baffle comprises a throttle baffle lower sheet, a throttle baffle upper sheet and a positioning bolt and a positioning nut; the two sides of the throttle baffle are provided with a left buckle and a right buckle, and the plate surface of the throttle baffle is provided with a plurality of through holes; the lower piece of the throttling baffle and the upper piece of the throttling baffle are respectively arranged on the upper side and the lower side of the flame tube and are inserted into baffle grooves on the flame tube. The lower piece of the throttling baffle plate is connected with the upper piece of the throttling baffle plate through a positioning bolt and a positioning nut. The lower sheets of the two adjacent throttle baffles and the upper sheets of the two adjacent throttle baffles are respectively lapped by a left buckle and a right buckle.
The invention has the beneficial effects that:
(1) The combustion chamber can be used for on-line regulating the distribution of the air inflow of the nozzle, the main combustion air quantity and the blending air quantity in the combustion chamber according to the characteristics of different phase fuels in the whole operation process of the gas turbine, so that the high-quality compatible gas fuel and liquid fuel (low-emission combustion of the gas fuel, high-efficiency combustion of the liquid fuel and high uniformity of the gas temperature) of the gas turbine are realized
(2) Meanwhile, the machining precision tolerance of the combustion chamber to the flow area of the nozzle and the flame tube is high, and the machining debugging cost and the cycle are lower.
Drawings
FIG. 1 is a schematic cross-sectional view of the present invention;
FIG. 2 is a partial cross-sectional view and a partial enlarged view of FIG. 1;
FIG. 3 is an exploded view of a combustion chamber with an air conditioning system according to the present invention;
FIG. 4 is a schematic cross-sectional view of derivative structures of several air conditioning systems of the present invention.
In the figure: 1-bleed air passage; 1-1-bleed air channel piping; 1-2-bleed air flow regulating valve; 2-a throttle baffle; 2-1-throttling baffle plate lower plate; 2-2-throttling baffle upper piece; 2-3-left side buckle; 2-4-right side buckle; 2-5-through holes; 2-6-positioning bolts and nuts; 3-a combustion chamber housing; 3-1-combustion chamber air inlet; 3-2-combustion chamber outlet; 3-3-outer casing; 3-4-inner casing; 4-dual fuel nozzle; 5-a flame tube; 5-1-a main combustion hole of the flame tube; 5-2-a flame tube blending hole; 5-3-baffle plate groove.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, the dual-fuel low-emission gas turbine combustion chamber with an air conditioning system comprises a bleed air channel 1, a throttle baffle 2, a combustion chamber housing 3, a dual-fuel nozzle 4 and a flame tube 5; the air entraining channel 1 is arranged on the outer side of the combustion chamber shell 3, the throttle baffle 2, the dual-fuel nozzle 4 and the flame tube 5 are arranged on the inner side of the combustion chamber shell 3, the throttle baffle 2 is arranged in an interlayer between the flame tube 5 and the combustion chamber shell 3, a main combustion hole and a blending hole on the dual-fuel nozzle and the flame tube are divided into two areas, through-flow holes are formed in the throttle baffle according to the through-flow requirements of the two areas, a fuel outlet of the dual-fuel nozzle 4 is connected with the flame tube 5, and an outlet of the flame tube 5 is connected with the combustion chamber outlet 3-2.
The air entraining channel 1 comprises an air entraining channel pipeline 1-1 and an air entraining flow regulating valve 1-2, the air entraining channel pipeline 1-1 is welded on the combustion chamber shell 3, one end of the air entraining channel pipeline 1-1 is close to the combustion chamber air inlet 3-3, and the other end of the air entraining channel pipeline is far away from the combustion chamber inlet 3-3 and is positioned on the other side of the throttle baffle 2; the bleed air channel pipeline 1-1 is provided with a bleed air flow regulating valve 1-2 for regulating the air flow in the bleed air channel pipeline 1-1.
The wall surface of the flame tube 5 is provided with a flame tube main combustion hole 5-1 and a flame tube mixing hole 5-2, the outer side of the flame tube is provided with a baffle plate groove 5-3, and the baffle plate groove 5-3 is used for installing the fixed throttle baffle plate 2.
As shown in fig. 2, the throttle baffle 2 comprises a throttle baffle lower plate 2-1, a throttle baffle upper plate 2-2 and a positioning bolt nut 2-6, wherein both sides of the throttle baffle 2 are provided with a left side buckle 2-3 and a right side buckle 2-4, and the surface of the throttle baffle 2 is provided with a plurality of through holes 2-5. The lower baffle plate 2-1 and the upper baffle plate 2-2 are respectively arranged on the upper side and the lower side of the flame tube 5, are inserted into baffle grooves 5-3 on the flame tube 5, and clamp the flame tube 5 in the middle. The lower baffle plate 2-1 and the upper baffle plate 2-2 of the same flame tube 5 are connected through positioning bolts and nuts 2-6. The left side buckle 2-3 and the right side buckle 2-4 are overlapped between the lower pieces 2-1 of the two adjacent throttle baffles and between the upper pieces 2-2 of the two adjacent throttle baffles.
The through-flow performance of the throttle screen 2 is determined by the total area of the through-flow holes 2-5. The whole gas turbine is provided with a plurality of sets of throttle baffles 2 with different through-flow performances. In the stage of debugging and running-in of the gas turbine, the throttle baffle 2 with the best effect is selected according to the test result.
Air enters an interlayer between the combustion chamber shell 3 and the flame tube 5 from the combustion chamber outlet 3-2, and part of the air sequentially passes through the through holes 2-5 on the throttle baffle 2 and the dual-fuel nozzle 4 and enters the flame tube 5 to participate in combustion; the flame tube enters the flame tube 5 through the flame tube main combustion hole 5-1 and the flame tube mixing hole 5-2 to participate in combustion and temperature field adjustment; a part of air sequentially passes through the air entraining channel 1 and the dual-fuel nozzle 4 as required, and enters the flame tube 5 to participate in combustion; the air burns in the flame tube 5, and the fuel gas finally exits the combustion chamber through the combustion chamber outlet 3-2 and enters the downstream turbine to do work.
When the liquid fuel is used in the combustion chamber, the bleed air flow regulating valve 1-2 is closed, air can only enter the dual-fuel nozzle 4 through the through hole 2-5, less air enters the flame tube 5 through the dual-fuel nozzle 4, the liquid fuel can be fully combusted on the upstream of the flame tube 5 for a longer time, more air enters the flame tube 5 through the flame tube main combustion hole 5-1 and the flame tube blending hole 5-2 at the moment, and the uniformity of the temperature of the fuel gas reaching the combustion chamber outlet 3-2 can be effectively regulated.
When the combustion chamber uses gas fuel, the bleed air flow regulating valve 1-2 is opened, air enters the dual-fuel nozzle 4 through the bleed air channel 1 and the through holes 2-5, the air flow rate flowing through the dual-fuel nozzle is increased, namely the premixed air flow rate is increased, the temperature of the combustion zone is reduced, and the generation of pollutants is reduced; the air entering the flame tube 5 through the dual-fuel nozzle 4 is more, the gas fuel and enough air are fully mixed to realize low-emission combustion, the gas temperature uniformity of the premixed combustion of the gas fuel is higher, and even if the air entering the flame tube 5 through the flame tube main combustion hole 5-1 and the flame tube blending hole 5-2 is less, the requirement of a turbine at the downstream of the combustion chamber on the gas temperature uniformity can be met.
The combustor structure can adjust the air distribution of the combustor according to the fuel property, the state of the gas turbine unit and the atmospheric environmental condition, thereby reducing the processing precision requirement on the through-flow structure of the fuel nozzle and the flame tube and improving the adaptability of the combustor to fuel and air.
When the combustion chamber is in a low-load working condition, the bleed air flow regulating valve 1-2 is closed to reduce the air inlet flow of the dual-fuel nozzle 4 so as to avoid flameout of the combustion chamber.
As shown in fig. 4, a dual fuel low emission gas turbine combustor with an air conditioning system has a multiple derivative configuration. According to the combustion chamber air inlet type, when the combustion chamber air inlet is in a forward air flow air inlet type, the control logic of the air-entraining flow regulating valve 1-2 is opposite to that of the reverse air inlet combustion chamber. According to the specific requirements of the air control of the combustion chamber, multiple bleed air channels 1 and throttle baffle structures can be arranged, so that more accurate air control is realized. The throttle screen 2 may be fixed to the combustion chamber housing 3 in various types according to the overall layout of the combustion chamber; the throttle screen 2 may be of a single-piece or multi-piece construction.
The mounting positions and the working modes of the air entraining channels and the air entraining flow regulating valves are changed along with the structural type of the combustion chamber, and when the combustion chamber is in countercurrent air intake, the air entraining flow regulating valves are closed and reduced to reduce the air inflow of the nozzle; when the combustion chamber is in forward flow, the bleed air flow regulating valve is closed to reduce the air inflow of the nozzle, and the bleed air channel is used for communicating the spaces at the two sides of the throttle baffle, so that the function of regulating the air flow of the spaces at the two sides of the flow channel can be achieved.
The throttle baffle positions, the number and the connection types are changed according to the structure and the actual requirements of the combustion chamber: the throttle baffle plate comprises, but is not limited to, dividing a nozzle, a main combustion hole and a blending hole on the flame tube into two spaces, and dividing a nozzle multi-stage air inlet channel, a main combustion hole, a cooling hole and a blending hole on the flame tube into different spaces; the throttle screen version includes, but is not limited to, being secured to the flame tube, but may also be secured to the combustion chamber housing with a gap between the throttle screen and the flame tube.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A dual fuel low emission gas turbine combustor with air conditioning system, characterized by comprising a bleed air channel (1), a throttle baffle (2), a combustor casing (3), a dual fuel nozzle (4) and a flame tube (5); the air entraining channel (1) is arranged outside the combustion chamber shell (3); the throttle baffle (2), the dual-fuel nozzle (4) and the flame tube (5) are arranged on the inner side of the combustion chamber shell (3); the throttle baffle (2) is arranged in an interlayer between the flame tube (5) and the combustion chamber shell (3); the fuel outlet of the dual-fuel nozzle (4) is connected with the flame tube (5); the flame tube (5) is connected with the combustion chamber outlet (3-2).
2. A dual fuel low emission gas turbine combustor with an air conditioning system according to claim 1, characterized in that the bleed air channel (1) comprises a bleed air channel line (1-1) and a bleed air flow regulating valve (1-2); the air-entraining channel pipeline (1-1) is welded on the combustion chamber shell (3), one end of the air-entraining channel pipeline (1-1) is close to the combustion chamber air inlet (3-3), the other end of the air-entraining channel pipeline is far away from the combustion chamber inlet (3-3) and is positioned on the other side of the throttle baffle (2), the air-entraining channel pipeline (1-1) is provided with an air-entraining flow regulating valve (1-2), and the air flow in the air-entraining channel pipeline (1-1) is regulated.
3. A dual fuel low emission gas turbine combustor with air conditioning system according to claim 1, wherein the liner (5) wall is provided with liner main burner ports (5-1) and liner blending ports (5-2); the outside of the flame tube (5) is provided with a baffle groove (5-3), and the baffle groove (5-3) is used for installing and fixing the throttle baffle (2).
4. A dual fuel low emission gas turbine combustor with an air conditioning system according to claim 1, wherein the throttle plate (2) comprises a throttle plate lower plate (2-1), a throttle plate upper plate (2-2) and a positioning bolt nut (2-6); the two sides of the throttling baffle (2) are provided with a left side buckle (2-3) and a right side buckle (2-4), and the surface of the throttling baffle (2) is provided with a plurality of through holes (2-5); the lower baffle plate (2-1) and the upper baffle plate (2-2) are respectively arranged on the upper side and the lower side of the flame tube (5) and are inserted into baffle grooves (5-3) on the flame tube (5). The lower piece (2-1) of the throttling baffle and the upper piece (2-2) of the throttling baffle are connected through positioning bolts and nuts (2-6). The lower sheets (2-1) of the two adjacent throttle baffles and the upper sheets (2-2) of the two adjacent throttle baffles are respectively overlapped by a left buckle (2-3) and a right buckle (2-4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310915577.4A CN117053230A (en) | 2023-07-25 | 2023-07-25 | Dual-fuel low-emission gas turbine combustion chamber with air conditioning system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310915577.4A CN117053230A (en) | 2023-07-25 | 2023-07-25 | Dual-fuel low-emission gas turbine combustion chamber with air conditioning system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117053230A true CN117053230A (en) | 2023-11-14 |
Family
ID=88656333
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310915577.4A Pending CN117053230A (en) | 2023-07-25 | 2023-07-25 | Dual-fuel low-emission gas turbine combustion chamber with air conditioning system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117053230A (en) |
-
2023
- 2023-07-25 CN CN202310915577.4A patent/CN117053230A/en active Pending
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