CN108592083B - Combustion chamber adopting variable cross-section air inlet and multi-stage fuel supply and control method thereof - Google Patents
Combustion chamber adopting variable cross-section air inlet and multi-stage fuel supply and control method thereof Download PDFInfo
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- CN108592083B CN108592083B CN201810437323.5A CN201810437323A CN108592083B CN 108592083 B CN108592083 B CN 108592083B CN 201810437323 A CN201810437323 A CN 201810437323A CN 108592083 B CN108592083 B CN 108592083B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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Abstract
The invention discloses a combustion chamber adopting variable cross-section air intake and multi-stage fuel supply and a control method thereof, wherein the combustion chamber comprises a combustion chamber head and a flame tube, the combustion chamber head comprises a first fuel-air injection system and a second fuel-air injection system which is radially positioned at the outer side of the first fuel-air injection system, fuel is supplied into the first fuel-air injection system and the second fuel-air injection system in a staged manner, and fuel-air mixtures respectively injected by the first fuel-air injection system and the second fuel-air injection system are premixed and lean in fuel combustion in a two-stage interval in which the flame tubes are connected in parallel. The fuel premixing device is premixed with air through multi-stage fuel supply control, and can better adapt to the combustion of various fuels; the discharge of pollutants is reduced; the fuel can be simultaneously fed in different fuels according to proportion, the mixed combustion performance control is optimized, and the stability and the low-pollution emission performance of the premixed lean fuel combustion can be kept in a wider working range.
Description
Technical Field
The invention relates to the field of low-pollution combustion, in particular to a combustion chamber adopting variable-section air inlet and multi-stage fuel supply and a control method thereof.
Background
The ground gas turbine is widely applied to occasions closely related to the life of people, such as power plants, power machines, distributed energy supply, biomass gas and other fuel gas energy sources, and NO is applied to all countries in the worldXThe emission requirements of CO, UHC and the like are more and more strict,the technology of the low-pollution combustion chamber is promoted to be continuously developed. In order to seize the market and meet the increasingly strict pollution emission standard, various well-known engine companies in the world are intensively researching low-pollution technologies, on one hand, the low-pollution technologies are used for improving the competitiveness of products in the market, and on the other hand, the low-emission gas turbines are used for the future market. The ground gas turbine can control NO on the basis of a large number of experiments abroadXAnd the DLN combustion technology applied at present mainly comprises staged combustion, lean fuel premixing and pre-evaporation combustion (LPP), rich fuel/quenching/lean fuel combustion (RQL), catalytic combustion and the like.
The aeroengine is changed into the ground gas turbine or the ground gas turbine is developed by utilizing the mature core technology of the aeroengine, which is a common method in the industrialized developed countries in the world, China has the history of nearly forty years in the aspect of changing the aeroengine into the ground gas turbine, a lot of experience is accumulated, but the low-pollution emission technology research and the practical application are lagged behind, and the ground gas turbine mainly depends on import or domestic assembly production at present. With the improvement of the national emission standard requirements, research on low-pollution combustion technology is carried out successively in some scientific research institutions, universities and the like in China; but aiming at the alternative fuel under the background of energy conservation and emission reduction, the key design technology of the low-pollution combustion chamber of the small and medium-sized micro gas turbine which can adapt to biomass gas and multiple fuels has no major breakthrough in China, and has a great gap with developed countries.
The low-pollution combustion of domestic and foreign gas turbines and industrial combustors adopts the main defects of the prior premixed lean fuel combustion scheme as follows: 1) cannot simultaneously accommodate multiple fuels, such as biogas and natural gas; 2) the fuel nozzle or the flame tube head needs to be replaced aiming at fuels with different characteristics and heat values; 3) in the prior art, in order to ensure the stability of combustion and the flameout prevention of the working condition change of a gas turbine in the ignition starting and operation processes, an on-duty nozzle is generally required to be arranged, and the on-duty nozzle adopts a traditional diffusion combustion mode, so that a certain amount of pollutant emission is easily generated; 4) the adjusting range of the premixed stable combustion is small; 5) the air intake of the flame tube head cannot be changed according to the change of the working conditions of the gas turbine and the difference of the used fuel, so that the optimal fuel/air ratio parameter required for maintaining low-pollution combustion cannot be adjusted in a wide range; 6) when the operating condition and the fuel property change range are large, the combustion is easy to be unstable and pollutants are easy to be generated as follows: increase in emission of CO, NOx, UCH, etc.
Disclosure of Invention
The invention provides a combustion chamber adopting variable cross-section air inlet and multi-stage fuel supply and a control method thereof, which are used for solving the technical problems that pollutants are easy to generate and multi-fuel low-pollution stable combustion cannot be simultaneously adapted in the traditional diffusion combustion mode.
The technical scheme adopted by the invention is as follows:
according to one aspect of the present invention, there is provided a combustion chamber using variable cross-section intake air and multi-stage fuel supply, comprising a combustion chamber head and a flame tube, the combustion chamber head comprising a first fuel-air injection system and a second fuel-air injection system located radially outside the first fuel-air injection system, fuel being supplied in stages to the first fuel-air injection system and the second fuel-air injection system,
the first fuel air injection system comprises a fuel central air inlet pipe positioned outside the central ignition electric nozzle, a first-stage nozzle arranged on the fuel central air inlet pipe, an inner swirler arranged on the outer side of the fuel central air inlet pipe, and a second-stage nozzle, wherein the first-stage fuel is directly injected into the flame tube through the first-stage nozzle, the second-stage fuel is sprayed out through the second-stage nozzle, premixed with air entering the inner swirler and then injected into the flame tube in a lean fuel state in a swirling mode, and the first-stage fuel and the second-stage fuel enter the flame tube to realize first-stage interval combustion;
the second fuel air injection system comprises an outer swirler, a third-stage nozzle and a variable cross-section air inlet adjusting assembly, wherein the outer swirler is positioned on the outer side of the inner swirler, the variable cross-section air inlet adjusting assembly is arranged on the outer side of a channel where the outer swirler is positioned and positioned on the downstream of the outer swirler and used for adjusting the air inlet amount entering the downstream of the outer swirler, and the third-stage fuel is sprayed out through the third-stage nozzle, premixed with the air entering the outer swirler and the air entering from the variable cross-section air inlet adjusting assembly, and then sprayed into the flame tube in a lean fuel state in a swirling mode to realize second-stage interval combustion;
the fuel-air mixture respectively injected by the first fuel-air injection system and the second fuel-air injection system is subjected to premixed lean fuel combustion in a two-stage interval with parallel flame tubes.
And the second fuel air injection system also comprises a fourth stage nozzle, wherein fourth stage fuel is sprayed out through the fourth stage nozzle, premixed with air entering the outer swirler and air entering the self-variable section air inlet adjusting assembly and then injected into the flame tube in a lean fuel state in a swirling mode to realize second stage interval combustion.
Furthermore, the variable cross-section air inlet adjusting assembly comprises an air inlet flow channel piece and an air adjusting ring, wherein the air inlet flow channel piece is fixed outside the channel where the outer swirler is located, the air adjusting ring is sleeved on the periphery of the air inlet flow channel piece in a rotating mode, a plurality of air inlets are formed in the circumference of the air inlet flow channel piece, a plurality of through holes corresponding to the air inlets are formed in the air adjusting ring in the circumference of the air adjusting ring, and the overlapping degree of the through holes and the air inlets is changed when the air adjusting ring rotates relative to the air inlet flow.
Further, the cross-sectional area of the through-hole is tapered in the air intake direction;
the inlet cross-sectional area of the air inlet hole is equal to the outlet cross-sectional area of the through hole.
Further, the inner swirler has the same swirling direction as the outer swirler.
Furthermore, the first fuel-air injection system also comprises an inner flow passage arranged outside the fuel central air inlet pipe, and the inner swirler is connected with the inlet or the outlet of the inner flow passage;
the second fuel-air injection system further comprises an outer flow passage arranged on the outer side of the inner flow passage, and the outer swirler is connected to an inlet or an outlet of the outer flow passage.
According to another aspect of the present invention, there is also provided a control method applied to the combustion chamber employing variable-area intake and multi-stage fuel supply described above, including the steps of:
adjusting the air inlet section of the variable-section air inlet adjusting assembly to be fully closed to enable the air inlet quantity to be zero, and supplying fuel to a first-stage nozzle in a first fuel air injection system until the gas turbine is started;
when the gas turbine reaches a preset working condition, the second-stage nozzle in the first fuel-air injection system starts to gradually supply fuel, and the first-stage nozzle synchronously and gradually reduces the supply of the fuel, so that the first fuel-air injection system is switched to supply fuel-air mixture in a premixed lean state, and the air inlet section of the variable-section air inlet adjusting assembly is kept fully closed;
when the gas turbine is loaded, the opening degree of the air inlet section of the variable-section air inlet adjusting assembly is adjusted to gradually increase until the variable-section air inlet adjusting assembly is fully opened, and the second fuel air injection system is used for carrying out swirl injection on a fuel-air mixture in a premixed lean fuel state to the flame tube.
Further, adjusting the intake section of the variable-section intake air adjusting assembly includes:
the air adjusting ring of the variable-section air inlet adjusting assembly is controlled to rotate relative to the air inlet flow channel piece, so that the overlapping degree of the through hole and the air inlet hole is changed.
Further, in the case of a single-shaft gas turbine,
when fuel is high-heat value fuel, when the single-shaft gas turbine reaches an idle state, the first-stage nozzle is controlled to gradually reduce until fuel supply is stopped, meanwhile, the second-stage nozzle starts to synchronously supply fuel, enters the flame tube after being premixed with air through the inner swirler, and gradually and synchronously increases until the fuel is supplied to replace the first-stage nozzle, and in the adjusting process, the fuel increasing amount of the second-stage nozzle is synchronously equal to the fuel reducing amount of the first-stage nozzle, and the working state parameters of the gas turbine are unchanged;
when the fuel is medium and low calorific value fuel, the gas turbine is started, firstly, the first-stage nozzle supplies fuel, the second-stage nozzle starts to supply fuel after reaching a preset rotating speed, when the single-shaft gas turbine reaches an idle load state, the first-stage nozzle is controlled to gradually reduce the fuel supply, simultaneously, the second-stage nozzle starts to synchronously increase the fuel supply, the fuel is premixed with air through the inner swirler and then enters the flame tube, the fuel is gradually and synchronously increased until the fuel in the inner swirling first-stage combustion area is mainly supplied by the second-stage nozzle, and in the adjusting process, the fuel increasing amount of the second-stage nozzle is equal to the fuel decreasing amount of the first-stage nozzle, and the working state parameters of the gas.
Further, for split-shaft gas turbines,
when fuel is high-heat-value fuel, the split-shaft gas turbine starts to increase load after reaching an idle load state, at the moment, a second fuel air injection system starts to supply fuel, when the split-shaft gas turbine reaches 10% -45% load, a first-stage nozzle is controlled to gradually reduce until the fuel supply is stopped, meanwhile, a second-stage nozzle starts to synchronously supply fuel, enters a flame tube after being premixed with air through an inner swirler and gradually and synchronously increases until the fuel is supplied to replace the first-stage nozzle, and in the adjusting process, the fuel increase amount of the second-stage nozzle is equal to the fuel decrease amount of the first-stage nozzle, and the working state parameters of the gas turbine are unchanged;
when the fuel is low-heat value fuel, the split-shaft gas turbine is started and reaches a preset rotating speed, the fuel supplied by the first-stage nozzle is kept unchanged, and the fuel supplied by the second-stage nozzle is premixed with air through the inner swirler and then enters the flame tube until the split-shaft gas turbine reaches an idle state; and then, feeding fuel into the third-stage nozzle, controlling the first-stage nozzle to gradually reduce the fed fuel when the split-shaft gas turbine reaches 10% -45% of load, simultaneously, synchronously and gradually increasing the fed fuel into the second-stage nozzle, premixing the fuel with air through the inner swirler, and then feeding the fuel into the flame tube, and adjusting until the fuel in the inner swirling first-stage combustion zone is mainly fed by the second-stage nozzle, wherein in the adjusting process, the fuel increasing amount of the second-stage nozzle is equal to the fuel decreasing amount of the first-stage nozzle, and the working state parameters of the gas turbine are unchanged.
Further, under the load operation condition of the gas turbine, the optimal combustion and the lowest pollutant emission are realized by controlling and changing the fuel feeding proportion of the first-stage nozzle, the second-stage nozzle, the third-stage nozzle and the fourth-stage nozzle into the flame tube.
According to the invention, the mode that the first fuel air injection system and the second fuel air injection system respectively inject fuel-air mixtures to carry out premixed lean fuel parallel two-stage zone combustion in the flame tube is adopted, and the premixed lean fuel is adopted for staged zone combustion, and meanwhile, the fuel is supplied in multiple stages, so that the method can better adapt to low-pollution combustion of various fuels, including low-calorific-value fuel, and organizes low-pollution combustion; the first-stage combustion zone also adopts a low-pollution combustion mode of premixed lean fuel, and the diffusion combustion on duty is not needed, so that the emission of pollutants is reduced; the second-stage fuel air injection system adopts the variable cross-section air inlet adjusting component to adjust the air inlet amount, and keeps the fuel and air ratio to adapt to the high-efficiency low-pollution combustion condition under the conditions of a wider working condition range of the operation of the gas turbine and the use of fuels with different characteristics; the staged nozzles can realize simultaneous feeding of different fuels according to proportion, optimize mixed combustion performance control and realize low-pollution mixed combustion in the flame tube. The invention can better adapt to the combustion of various fuels by premixing with air through multi-stage fuel supply control; the discharge of pollutants is reduced; the gas turbine can realize simultaneous feeding of different fuels according to a proportion, optimize mixed combustion performance control, realize low-pollution mixed combustion in a flame tube, and maintain the stability and low-pollution emission performance of premixed lean fuel combustion in a wider working range by changing the air inlet sectional area of the head part of a combustion chamber and adjusting the air flow according to different working conditions and fuels with different characteristics of the gas turbine in the operation process.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic block diagram of a first embodiment of a combustion chamber of the present invention utilizing variable cross-section intake and multi-stage fuel supply;
FIG. 2 is a schematic structural view of a second embodiment of the combustion chamber of the present invention employing variable cross-section intake and multi-stage fuel supply;
FIG. 3 is a schematic structural view of a third embodiment of the combustion chamber of the present invention employing variable cross-section intake and multi-stage fuel supply;
FIG. 4 is a schematic structural diagram of a fourth embodiment of the combustion chamber of the present invention utilizing variable area intake and multi-stage fuel delivery;
FIG. 5 is a schematic cross-sectional view of the intake air adjustment assembly of FIG. 3 taken along line A-A, illustrating the fully open operational configuration of the intake ports;
FIG. 6 is a schematic view of the variable area intake air adjustment assembly in an operational state with the intake port partially open;
FIG. 7 is a schematic view of the variable cross section intake air adjustment assembly when the intake ports are fully closed.
The reference numbers illustrate:
1. a combustion chamber head; 10. an ignition torch; 11. a fuel center inlet pipe; 110. a first stage nozzle; 12. an inner swirler; 13. a second stage nozzle; 14. an outer swirler; 15. a third stage nozzle; 16. a fourth stage nozzle; 17. an inner flow passage; 18. an outer flow passage; 2. a flame tube; 3. a variable cross-section air intake adjustment assembly; 30. an inlet flow channel member; 301. an air inlet; 31. a gas regulating ring; 311. And a through hole.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1, a first embodiment of the present invention provides a combustion chamber using variable-area intake and multi-stage fuel supply, including a combustion chamber head 1 and a flame tube 2, the combustion chamber head 1 including a first fuel-air injection system and a second fuel-air injection system located radially outside the first fuel-air injection system, and fuel being supplied in stages to the first fuel-air injection system and the second fuel-air injection system. In the combustion chamber suitable for multiple fuels, a first fuel-air injection system and a second fuel-air injection system both have premixing functions, and fuel-air mixtures respectively injected by the first fuel-air injection system and the second fuel-air injection system are premixed and lean in fuel combustion in a two-stage parallel combustion area formed in a flame tube 2.
Specifically, the first fuel-air injection system includes a fuel center inlet pipe 11 located outside the center ignition electric nozzle 10, a first-stage nozzle 110 provided on the fuel center inlet pipe 11, an inner swirler 12 provided outside the fuel center inlet pipe 11, and a second-stage nozzle 13.
In this embodiment, the first-stage nozzle 110 is disposed on the peripheral wall of the fuel central inlet pipe 11, and includes a plurality of nozzle holes uniformly distributed along the circumference, forming a multi-point injection. The first stage fuel is injected directly into the combustor basket 2 through the first stage nozzle 110.
In this embodiment, the inner swirler 12 is an axial flow swirler. The second stage nozzle 13 is located upstream of the inner swirler 12 and directly opposite the inner swirler 12. The secondary fuel is injected into the vane passage of the inner swirler 12 through the secondary nozzle 13, premixed with the air entering the inner swirler 12, and then swirl-injected into the combustor basket 2 in a lean fuel state. The first stage fuel and the second stage fuel enter the first stage combustion area of the flame tube 2 to realize the first stage interval combustion.
The second fuel air injection system includes an outer swirler 14 located outside the inner swirler 12, a tertiary nozzle 15, and a variable area inlet modulation assembly 3. The variable cross-section air intake regulating assembly 3 is arranged outside the passage of the outer swirler 14 and downstream of the outer swirler 14, and is used for regulating the air intake amount entering the downstream of the outer swirler 14. In this embodiment, the tertiary nozzles 15 are disposed on the sidewall of the outer swirler 14. The third stage fuel is sprayed into the vane channel of the outer swirler 14 through the third stage nozzle 15, premixed with the air entering the outer swirler 14 and the air entering from the variable cross-section air inlet adjusting assembly 3, and then swirlingly sprayed into the flame tube 2 in a lean fuel state, so that second stage interval combustion is realized in the second stage combustion zone. In this embodiment, the outer swirler 14 is also an axial flow swirler.
Further, in the present embodiment, the second fuel-air injection system further includes a fourth stage nozzle 16. In this embodiment, the fourth stage nozzle 16 is also disposed on the sidewall of the outer swirler 14. The fourth stage fuel is sprayed into the vane channel of the outer swirler 14 through the fourth stage nozzle 16, premixed with the air entering the outer swirler 14 and the air entering from the variable cross-section air inlet adjusting assembly 3, and then swirled and sprayed into the flame tube 2 in a lean fuel state, so that second stage interval combustion is realized in the second stage combustion zone. In this embodiment, the second stage fuel is premixed with the air entering the inner swirler 12 and then swirled and injected from the inner swirler 12 into the combustor basket 2 in a lean state, and the third and fourth stage fuels are premixed with the air entering the outer swirler 14 and the air entering from the variable cross-section intake air adjusting assembly 3 and then swirled and injected from the outer swirler 14 into the combustor basket 2 in a lean state.
The two groups of nozzles, namely the third-stage nozzle 15 and the fourth-stage nozzle 16, jointly spray fuel into the channel of the outer swirler 14, so that the flow rate of the fuel is favorably adjusted and controlled in a larger range, and the premixing characteristic of the fuel is ensured in a larger adjustment range (the relative speed of the fuel and air is kept in a certain range, and the like, so that premixing and blending are favorably realized.
In the first fuel-air injection system of the present invention, the first-stage nozzle 110 and the second-stage nozzle 13 can supply two different fuels, respectively, to realize multi-fuel mixed low-pollution combustion. The four-stage fuel supply channel and the nozzle can be respectively introduced with fuels with the same characteristics, and can also be respectively introduced with fuels with different characteristics for premixing low-pollution combustion. The fuel is any one of natural gas, biomass gasified gas, methane, coal bed gas, coal gas, shale gas, petroleum gas, landfill gas and other gas fuels.
Further, the first-stage nozzle 110, the second-stage nozzle 13, the third-stage nozzle 15, and the fourth-stage nozzle 16 each include a plurality of nozzle holes that are evenly distributed along the circumference. The structure can form multi-point injection and mix with air, and fuel and air enter the flame tube 2 after being premixed.
Further, in the present embodiment, the inner swirler 12 and the outer swirler 14 have the same swirling direction, which is beneficial for stable combustion.
Referring to fig. 1 and 5, the variable cross-section inlet adjustment assembly 3 includes an inlet flow channel member 30 fixed outside the channel of the outer swirler 14 and an air adjustment ring 31 rotatably sleeved on the periphery of the inlet flow channel member 30. The intake runner 30 has a plurality of intake holes 301 formed along the circumference. The plurality of air intake holes 301 are uniformly arranged. The air inlet holes 301 may be round holes or square holes. A plurality of through holes 311 corresponding to the air inlet holes 301 are formed along the circumference of the air adjusting ring 31. The plurality of through holes 311 are uniformly arranged. The through holes 311 may be circular holes or square holes, and have the same size and number as the intake holes 301 of the intake runner 30. When the air adjusting ring 31 rotates relative to the inlet runner 30, the overlapping degree of the through hole 311 and the inlet hole 301 changes to change the inlet cross-sectional area, thereby achieving the purpose of adjusting the inlet air flow.
Optionally, the cross-sectional area of the through-hole 311 tapers in the air intake direction. The sectional area of the inlet of the through hole 311 is larger than that of the outlet thereof, so that the resistance of the inlet of the outer ring of the through hole 311 to air can be reduced, and the air can smoothly enter the air inlet hole 301 to be effectively mixed with fuel. In other embodiments, the cross-sectional area of the through-hole 311 may remain constant, i.e., the inlet cross-sectional area of the through-hole 311 is equal to its outlet cross-sectional area. The sectional area of the inlet of the air inlet hole 301 is equal to or smaller than the sectional area of the outlet of the through hole 311, so that the air inlet hole 301 and the through hole 311 are well connected and are completely opened when the variable-section air inlet adjusting assembly 3 is fully opened, the air resistance is reduced, and the air utilization rate is improved.
Referring to fig. 2, a second embodiment of the present invention is substantially the same as the first embodiment except that: the first fuel-air injection system further includes an inner flow passage 17 disposed outside the fuel central air inlet pipe 11, the inner swirler 12 is connected to a position close to the outlet of the inner flow passage 17, that is, a position close to the combustor basket 2, the inner swirler 12 is an axial flow swirler, and the second stage nozzle 13 is disposed on a side wall of the inner flow passage 17 and located upstream of the inner swirler 12. It is also different in that: the second fuel-air injection system further includes an outer flow passage 18 disposed outside the inner flow passage 17, the outer swirler 14 is connected to an inlet position of the outer flow passage 18, the outer swirler 14 is a radial swirler, the third stage nozzle 15 and the fourth stage nozzle 16 are disposed on a sidewall of the outer swirler 14, and the inlet flow passage member 30 is fixedly mounted on an outer sidewall of the outer flow passage 18 and is close to an outlet of the outer flow passage 18. In this embodiment, the second stage fuel is premixed with the air entering the inner swirler 12 from the inner flow passage 17 and then swirled and injected into the combustor basket 2 from the inner swirler 12, and the third and fourth stage fuels are premixed with the air entering the outer swirler 14 and the air entering from the variable cross-section air intake adjusting assembly 3, respectively, and then swirled and injected into the combustor basket 2 from the outer flow passage 18.
Referring to fig. 3, a third embodiment of the present invention is substantially the same as the second embodiment except that: the inner swirler 12 is a radial swirler, the inner swirler 12 is connected at the inlet position of the inner flow passage 17, and the second stage nozzle 13 is arranged on the side wall of the inner flow passage 17 and downstream of the inner swirler 12. In this embodiment, the second stage fuel is premixed with air and swirled out from the inner flow path 17, and the third and fourth stage fuels are premixed with air and swirled out from the outer flow path 18. Of course, the second stage nozzle 13 may be disposed on the sidewall of the inner swirler 12, and the third stage nozzle 15 and the fourth stage nozzle 16 may be disposed on the sidewall of the outer flow passage 18. The invention is not limited thereto.
Referring to fig. 4, a fourth embodiment of the present invention is substantially the same as the third embodiment except that: the outer swirler 14 is an axial flow swirler, the outer swirler 14 is connected at an outlet position close to the outer flow passage 18, the third stage nozzle 15 and the fourth stage nozzle 16 are arranged on the side wall of the outer flow passage 18 and located at the upstream of the outer swirler 14, and the air inlet flow passage member 30 is arranged on the outer side wall of the outer flow passage 18 and located at the downstream of the outer swirler 14. Of course, the third stage nozzle 15 and the fourth stage nozzle 16 may also be provided on the side wall of the outer swirler 14. The invention is not limited thereto.
The combustion chamber suitable for multi-fuel low-pollution emission can be applied to a gas turbine, and can also be applied to industrial combustors, such as low-pollution energy-saving combustion equipment of thermal equipment for low-pollution metallurgical industrial furnaces, petrochemical industrial furnaces, boilers, environment-friendly pollutant treatment furnaces, biomass renewable energy source application and the like.
According to another aspect of the present invention, there is also provided a control method applied to the combustion chamber employing variable-area intake and multi-stage fuel supply described above, including the steps of:
adjusting the air inlet section of the variable-section air inlet adjusting assembly 3 to be fully closed to enable the air inlet quantity to be zero, and supplying fuel to a first-stage nozzle 110 in a first fuel air injection system until the gas turbine is started;
when the gas turbine reaches a preset working condition, the second-stage nozzle 13 in the first fuel-air injection system starts to gradually supply fuel, and the first-stage nozzle 110 synchronously and gradually reduces the supply of the fuel, so that the first fuel-air injection system is switched to supply fuel-air mixture in a premixed lean fuel state, and the air inlet section of the variable-section air inlet adjusting assembly 3 is kept fully closed; in this step, the working state parameters of the gas turbine are not changed during the fuel supply conversion process;
when the gas turbine is loaded, the air inlet section of the variable-section air inlet adjusting assembly 3 is adjusted, the opening degree is gradually increased along with the increase of the gas turbine load and fuel until the variable-section air inlet adjusting assembly is fully opened, and the second fuel air injection system supplies fuel air mixture in a premixed lean fuel state to the flame tube 2 in a swirl injection mode.
Specifically, the adjusting the air intake section of the variable-section air intake adjusting assembly 3 includes: the air adjusting ring 31 of the variable cross-section air inlet adjusting assembly 3 is controlled to rotate relative to the air inlet flow channel member 30, so that the overlapping degree of the through hole 311 and the air inlet hole 301 is changed. As shown in fig. 7, 6 and 5.
Referring to fig. 1, for a single-shaft gas turbine, the multi-stage fuel supply premixing and control process is specifically as follows:
firstly, the rotating speed of the single-shaft gas turbine starts to rise under the driving of the starting motor, the ignition electric nozzle 10 works, the first-stage nozzle 110 starts to spray fuel when the single-shaft gas turbine reaches a certain rotating speed, the fuel is sprayed in an increasing mode after the ignition is successful, and the rotating speed of the single-shaft gas turbine gradually increases until the starting is finished to be in an unloaded state.
① when the single-shaft gas turbine reaches the idling state when the fuel is high-calorific-value fuel such as natural gas, the first fuel-air injection system is controlled to be switched to a fuel-air mixture which is completely supplied with premixed lean fuel, the first-stage nozzle 110 is controlled to gradually decrease until the fuel supply is stopped, meanwhile, the second-stage nozzle 13 starts to synchronously supply fuel, the fuel is premixed with air through the inner swirler 12 and then enters the flame tube 2, the fuel is gradually and synchronously increased until the fuel is supplied to the first-stage nozzle 110, and the fuel increase amount of the second-stage nozzle 13 is equal to the fuel decrease amount of the first-stage nozzle 110 in the adjusting process and the working state parameter of the gas turbine is not.
② when the fuel is low heat value fuel such as biomass gas, the gas turbine is started, firstly the first stage nozzle 110 supplies fuel, the second stage nozzle 13 starts to supply fuel after reaching the preset speed, when the single-shaft gas turbine reaches the idle state, the first fuel air injection system is controlled to be changed into the fuel air mixture mainly supplying premixed fuel and lean fuel, the first stage nozzle 110 is controlled to gradually reduce to reserve and supply a small amount of fuel, simultaneously the second stage nozzle 13 starts to synchronously increase to supply fuel and enters the flame tube 2 after being premixed with air through the inner swirler 12, and gradually and synchronously increases until the fuel in the inner swirling first stage combustion area is mainly supplied by the second stage nozzle 13, namely, the fuel supplied by the second stage nozzle 13 is adjusted to be more than 50% of the fuel supplied by the first fuel air injection system, the fuel increase amount of the second stage nozzle 13 is equal to the fuel decrease amount of the first stage nozzle 110 in the adjusting process, and the working state parameter of the gas turbine is not changed.
When the single-shaft gas turbine is loaded, the air adjusting ring 31 is rotated to ensure that the opening degree of the air inlet section of the air inlet hole 301 is gradually increased along with the increase of the load and fuel of the gas turbine, and the second fuel air injection system performs rotational flow injection on air-fuel mixed combustible gas in a premixed and lean fuel state to the flame tube 2: one of the tertiary nozzle 15 or the fourth nozzle 16 is supplied with fuel and premixed with air entering the outer swirler 14 and air entering from the variable area air intake adjusting assembly 3 to swirl and inject in a lean state into the combustor basket 2. At this time, the fuel-air mixtures injected by the first fuel-air injection system and the second fuel-air injection system, respectively, undergo premixed lean combustion in the two-stage parallel combustion zone formed in the combustor basket 2.
The load increase and the load decrease of the single-shaft gas turbine are realized by adjusting the fuel feeding amount of the second fuel air injection system. Specifically, when high-calorific-value fuel such as natural gas is used as the fuel, only one of the third-stage nozzle 15 and the fourth-stage nozzle 16 needs to be put into operation, the load adjustment is realized by adjusting the increase and decrease of the amount of fuel supplied by the third-stage nozzle 15 or the fourth-stage nozzle 16, and accordingly, the air intake section opening of the air intake hole 301 can be correspondingly increased or decreased. When the fuel is a medium-low calorific value fuel such as biomass gas, the load adjustment is performed by adjusting the increase and decrease of the amount of fuel supplied from the third stage nozzle 15 and the fourth stage nozzle 16. This supply air regulation comprises two schemes: a) the amounts of fuel supplied to the third stage nozzle 15 and the fourth stage nozzle 16 are adjusted simultaneously; b) firstly, one of the third stage nozzle 15 and the fourth stage nozzle 16 is adjusted to start to operate and supply fuel, and when the opening degree of the control valve of one of the third stage nozzle 15 and the fourth stage nozzle 16 which is firstly operated is larger than or equal to about 95%, the other of the third stage nozzle 15 and the fourth stage nozzle 16 starts to operate and carries out load adjustment.
When the load of the single-shaft gas turbine is reduced from high to low to no load, the third-stage nozzle 15 or the fourth-stage nozzle 16 stops supplying fuel, the opening degree of the air inlet hole 301 is gradually reduced to full close along with the reduction of the load and the fuel flow, and only the first fuel air injection system supplies fuel from the second-stage nozzle 13 to realize premixed lean fuel combustion (when high-calorific-value or medium-calorific-value fuel is used); when the medium to low calorific value fuel is combusted, the first-stage nozzle 110 is supplied with a small amount of fuel at that time, and most of the fuel is supplied from the second-stage nozzle 13.
Referring also to FIG. 1, for a split-shaft gas turbine, the multi-stage fuel-feed premixing and control process is embodied as follows:
① when the fuel is high heating value fuel such as natural gas, the first stage nozzle 110 is supplied with fuel to start the split shaft gas turbine to an idling state, when the load is added, the fuel is supplied from one of the third stage nozzle 15 or the fourth stage nozzle 16 installed on the outer swirler 14, the air adjusting ring 31 is rotated to gradually increase the opening degree of the air intake section of the air intake port 301 with the increase of the load and the fuel flow rate, the fuel is premixed with the air entering the outer swirler 14 and the air entering from the variable section air intake adjusting assembly 3 and then injected into the flame tube 2, when the split shaft gas turbine reaches about 10% to 45% of the load, the first fuel air injection system is controlled to be supplied with fuel in a fully lean premixed state, the first stage nozzle 110 is controlled to gradually decrease the fuel supply until the fuel supply is stopped, the second stage nozzle 13 is simultaneously supplied with fuel and premixed with air after being premixed with air by the inner swirler 12 and then supplied into the flame tube 2, and the fuel is gradually and synchronously increased until the fuel is supplied to the first stage nozzle 110, when the fuel injection system is controlled to be supplied with a slightly increased load, the fuel injection system is controlled to a partially lean fuel injection system, and when the fuel injection system is supplied with the fuel injection system is controlled to a fully lean air and the air is supplied with a partially premixed fuel injection system is controlled to a fully lean fuel injection condition that the air injection system is changed to a certain amount is changed to a predetermined lean fuel injection.
② when fuel is low calorific value fuel such as biomass gas, the first stage nozzle 110 is supplied with fuel to ignite and increase the fuel flow gradually, the split shaft gas turbine reaches a predetermined speed, the second stage nozzle 13 starts to supply fuel and mixes with air through the inner swirler 12 and enters the flame tube 2 until the split shaft gas turbine reaches an idling state, when loading, the second fuel air injection system supplies fuel-air mixture in premixed lean fuel state to the flame tube 2, the air injection ring 31 is rotated to increase the opening degree of the air inlet 301 gradually with the increase of the load and the fuel flow, the fuel is premixed with the air entering the outer swirler 14 and the air entering from the variable cross-section air inlet adjusting assembly 3 and enters the flame tube 2, when the split shaft gas turbine reaches about 10% -45% load, the first fuel air injection system is controlled to supply fuel-air mixture in mainly premixed lean fuel state, the first stage nozzle 110 is controlled to be gradually reduced to a small amount, the second stage nozzle 13 starts to supply fuel-air mixture in premixed fuel state through the first stage nozzle 13 and the first stage nozzle 13 is controlled to increase in proportion to the flame tube 13, and the air injection process is controlled to increase gradually with the air injection ratio of the fuel-air injection and the flame injection system and the fuel-air injection process.
Similarly to the single-shaft gas turbine, the load adjustment and the load reduction of the split-shaft gas turbine are also realized by adjusting the fuel feeding amount of the second fuel air injection system, and accordingly, the opening degree of the air inlet section of the adjustable air inlet hole 301 is correspondingly increased or decreased. The split shaft gas turbine stops supplying fuel to the third-stage nozzle 15 or the fourth-stage nozzle 16 when the load is reduced to 10% -45% from high to low, and only the first fuel air injection system supplies fuel to the second-stage nozzle 13 to realize premixed lean fuel combustion.
Further, the first stage nozzle 110, the second stage nozzle 13, the third stage nozzle 15 and the fourth stage nozzle 16 are independent respectively, the fuel feeding of the nozzles at all stages is the same or different, and the control is carried out under the load operation condition of the gas turbineThe fuel feeding proportion of the first-stage nozzle 110, the second-stage nozzle 13, the third-stage nozzle 15 and the fourth-stage nozzle 16 into the flame tube 2 is changed, so that the optimal combustion and the lowest pollutant emission are realized. The fuel is any one of natural gas, biomass gasified gas, landfill gas, methane, coal bed gas, coal gas, shale gas, petroleum gas and other gas fuels. The high-calorific-value fuel refers to fuel with higher lower calorific value, and conversely, the high-calorific-value fuel refers to low-calorific-value fuel. Taking natural gas as an example, the natural gas belongs to high-calorific-value fuel, and the standard low-grade calorific value of the natural gas is 8500kcal/NM3And the lower calorific value of other medium calorific value fuels is about half of that of natural gas.
The invention has the following beneficial effects:
1) while the premixed lean fuel is adopted for staged combustion, the fuel is fed in multiple stages and is combusted in a partitioned mode, and the head of the flame tube chamber is adjusted by air inlet flow, so that the flame tube chamber can be better suitable for combustion of various fuels, including low-heat-value fuel, and low-pollution combustion is organized;
2) corresponding to a first fuel-air injection system, fuel and air come from an inner runner 17 (or an inner swirler 12), a first-stage nozzle 110 and a second-stage nozzle 13, the fuel is supplied into the flame tube 2 in a two-stage mode of directly injecting the first-stage fuel and injecting the second-stage fuel into the inner runner 17 or the inner swirler 12 for carrying out lean fuel premixing, and aiming at different working conditions and different fuels used by the gas turbine, the pollutant emission can be further reduced while stable combustion is realized by adjusting the supply proportion of the corresponding two-stage fuel in the first fuel-air injection system, and compared with the prior art of the same kind, the combustion stability is better, and the environmental protection performance is better; the first fuel-air injection system adopts a low-pollution mode of premixing lean fuel, and can further reduce the emission of pollutants on the basis of the prior art;
3) when the gas turbine operates stably with load, all premixed lean fuel can be supplied, and on-duty diffusion combustion is not needed, so that the emission of pollutants is reduced;
4) the air intake quantity of the head of the combustion chamber can be controlled and adjusted according to the working condition of the gas turbine and the fuel characteristic condition, and the fuel/air ratio can be kept in an optimized design interval in a large working range;
5) the low-pollution combustion can be realized in a wider working condition range, the stable low-pollution combustion adjusting range is large, the stable combustion range of a lean fuel boundary is wider, and the performances of spontaneous combustion, tempering and oscillatory combustion prevention are stronger;
6) corresponding to a second fuel-air injection system, fuel and air come from an outer flow passage 18 (or an outer swirler 14), the fuel is supplied in two stages by adopting a third-stage nozzle 15 and a fourth-stage nozzle 16, lean fuel premixing is carried out in the outer flow passage 18 or the outer swirler 14 and then enters the flame tube 2, the supply amount of the two-stage fuel is adjusted according to different working conditions of the gas turbine and different fuels used, and the entering amount of the air is adjusted by a variable-section air inlet adjusting assembly, so that the adjustment of the fuel with different characteristics in a wider range can be adapted;
7) the fuel can be simultaneously fed in different fuels according to the proportion, the feeding proportion can be steplessly adjusted, the mixed combustion performance control is optimized, and the low-pollution mixed combustion is realized in the flame tube 2.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (11)
1. A combustion chamber with variable cross-section air intake and multi-stage fuel supply, comprising a combustion chamber head (1) and a flame tube (2), characterized in that the combustion chamber head (1) comprises a first fuel-air injection system and a second fuel-air injection system located radially outside the first fuel-air injection system, fuel is supplied in stages to the first fuel-air injection system and the second fuel-air injection system,
the first fuel air injection system comprises a fuel central air inlet pipe (11) positioned outside a central ignition electric nozzle (10), a first-stage nozzle (110) arranged on the fuel central air inlet pipe (11), an inner swirler (12) arranged on the outer side of the fuel central air inlet pipe (11) and a second-stage nozzle (13), wherein first-stage fuel is directly injected into the flame tube (2) through the first-stage nozzle (110), second-stage fuel is sprayed out through the second-stage nozzle (13), premixed with air entering the inner swirler (12) and then injected into the flame tube (2) in a fuel-lean state in a swirling mode, and the first-stage fuel and the second-stage fuel enter the flame tube (2) and are used for realizing first-stage interval combustion;
the second fuel air injection system comprises an outer swirler (14) positioned on the outer side of the inner swirler (12), a third-stage nozzle (15) and a variable-section air inlet adjusting assembly (3), wherein the variable-section air inlet adjusting assembly (3) is arranged on the outer side of a channel where the outer swirler (14) is positioned, is positioned on the downstream of the outer swirler (14) and is used for adjusting the air inlet amount entering the downstream of the outer swirler (14), and third-stage fuel is sprayed out through the third-stage nozzle (15), premixed with air entering the outer swirler (14) and air entering from the variable-section air inlet adjusting assembly (3), and then sprayed into the flame tube (2) in a lean fuel state to realize second-stage interval combustion;
the fuel-air mixture respectively injected by the first fuel-air injection system and the second fuel-air injection system is subjected to premixed lean combustion in a two-stage interval in which the flame tubes (2) are connected in parallel.
2. The combustion chamber of claim 1,
the second fuel-air injection system also comprises a fourth stage nozzle (16), wherein fourth stage fuel is sprayed out through the fourth stage nozzle (16) and premixed with air entering the outer swirler (14) and air entering from the variable-section air inlet adjusting assembly (3) and then is subjected to swirl injection in a fuel-lean state into the flame tube (2) for realizing second stage interval combustion.
3. The combustion chamber of claim 1,
the variable cross-section air inlet adjusting assembly (3) comprises an air inlet flow channel piece (30) fixed outside a channel where an outer swirler (14) is located and an air adjusting ring (31) rotatably sleeved on the periphery of the air inlet flow channel piece (30), wherein the air inlet flow channel piece (30) is circumferentially provided with a plurality of air inlet holes (301), the air adjusting ring (31) is circumferentially provided with a plurality of through holes (311) corresponding to the air inlet holes (301), and when the air adjusting ring (31) rotates relative to the air inlet flow channel piece (30), the overlapping degree of the through holes (311) and the air inlet holes (301) is changed so as to change the air inlet cross-sectional area.
4. The combustion chamber of claim 3,
the cross-sectional area of the through hole (311) is tapered along the air inlet direction;
the inlet cross-sectional area of the air inlet hole (301) is equal to the outlet cross-sectional area of the through hole (311).
5. The combustion chamber of claim 1,
the inner swirler (12) and the outer swirler (14) have the same swirling direction.
6. The combustion chamber of claim 1,
the first fuel-air injection system further comprises an inner runner (17) arranged on the outer side of the fuel central air inlet pipe (11), and the inner swirler (12) is connected to the inlet or the outlet of the inner runner (17);
the second fuel-air injection system further comprises an outer flow passage (18) arranged outside the inner flow passage (17), and the outer swirler (14) is connected to an inlet or an outlet of the outer flow passage (18).
7. A control method applied to a combustion chamber using variable-area intake and multi-stage fuel supply according to any one of claims 1 to 6, characterized by comprising the steps of:
adjusting the air inlet section of the variable-section air inlet adjusting assembly (3) to be fully closed to enable the air inlet quantity to be zero, and enabling the first-stage nozzle (110) in the first fuel-air injection system to supply fuel until the gas turbine is started;
when the gas turbine reaches a preset working condition, the second-stage nozzle (13) in the first fuel-air injection system starts to gradually supply fuel, the first-stage nozzle (110) gradually reduces the supply of the fuel synchronously, so that the first fuel-air injection system is switched to supply fuel-air mixture in a premixed lean fuel state, and the air inlet section of the variable-section air inlet adjusting assembly (3) is kept fully closed;
when the gas turbine is loaded, the opening degree of the air inlet section of the variable-section air inlet adjusting assembly (3) is adjusted to gradually increase until the variable-section air inlet adjusting assembly is fully opened, and the second fuel air injection system is used for carrying out rotational flow injection on a fuel-air mixture in a premixed lean fuel state to the flame tube (2).
8. The control method according to claim 7, characterized in that said adjusting the intake section of said variable-section intake air adjusting assembly (3) comprises:
and controlling the air adjusting ring (31) of the variable-section air inlet adjusting assembly (3) to rotate relative to the air inlet flow channel member (30) so that the overlapping degree of the through hole (311) and the air inlet hole (301) is changed.
9. The control method according to claim 7, wherein, for a single-shaft gas turbine,
when fuel is high-heating-value fuel, when the single-shaft gas turbine reaches an idling state, the first-stage nozzle (110) is controlled to gradually reduce until fuel supply is stopped, meanwhile, the second-stage nozzle (13) starts to synchronously supply fuel, enters the flame tube (2) after being premixed with air through the inner swirler (12), and gradually and synchronously increases until the fuel is supplied to replace the first-stage nozzle (110), and in the adjusting process, the fuel increasing amount of the second-stage nozzle (13) is synchronously equal to the fuel decreasing amount of the first-stage nozzle (110) and the working state parameter of the gas turbine is unchanged;
when the fuel is medium and low calorific value fuel, the gas turbine is started, firstly, the first-stage nozzle (110) supplies fuel, the second-stage nozzle (13) starts to supply fuel after reaching a preset rotating speed, when the single-shaft gas turbine reaches an idle state, the first-stage nozzle (110) is controlled to gradually reduce the fuel supply, simultaneously, the second-stage nozzle (13) starts to synchronously increase the fuel supply, the fuel enters the flame tube (2) after being premixed with air through the inner swirler (12), and the fuel is gradually and synchronously increased until the fuel in the inner swirling first-stage combustion area is mainly supplied by the second-stage nozzle (13), and in the adjusting process, the fuel increasing amount of the second-stage nozzle (13) is equal to the fuel decreasing amount of the first-stage nozzle (110) and the working state parameter of the gas turbine is unchanged.
10. The control method according to claim 7, wherein, for a split shaft gas turbine,
when fuel is high-heat-value fuel, the split-shaft gas turbine starts to increase load after reaching an idle state, at the moment, a second fuel air injection system starts to supply fuel, when the split-shaft gas turbine reaches 10% -45% load, a first-stage nozzle (110) is controlled to gradually reduce until the fuel supply is stopped, meanwhile, a second-stage nozzle (13) starts to synchronously supply fuel, enters a flame tube (2) after being premixed with air through an inner swirler (12), and gradually and synchronously increases until the fuel is supplied to replace the first-stage nozzle (110), and in the adjusting process, the fuel increasing amount of the second-stage nozzle (13) is equal to the fuel decreasing amount of the first-stage nozzle (110) and the working state parameter of the gas turbine is unchanged;
when the fuel is medium and low calorific value fuel, after the split-shaft gas turbine is started and reaches a preset rotating speed, the fuel supplied by the first-stage nozzle (110) is kept unchanged, the fuel supplied by the second-stage nozzle (13) is started and premixed with air through the inner swirler (12), and then enters the flame tube (2) until the split-shaft gas turbine reaches an idle state; and then, the third-stage nozzle (15) starts to supply fuel, when the split-shaft gas turbine reaches 10% -45% load, the first-stage nozzle (110) is controlled to gradually reduce the fuel supply, meanwhile, the second-stage nozzle (13) starts to synchronously and gradually increase the fuel supply, the fuel enters the flame tube (2) after being premixed with air through the inner swirler (12), the fuel is adjusted until the fuel in the first-stage combustion zone of the inner swirler is mainly supplied by the second-stage nozzle (13), and in the adjusting process, the fuel increase amount of the second-stage nozzle (13) is equal to the fuel decrease amount of the first-stage nozzle (110) and the working state parameter of the gas turbine is unchanged.
11. The control method according to claim 7,
under the working condition of load operation of the gas turbine, the optimal combustion and the lowest pollutant emission are realized by controlling and changing the fuel feeding proportion of the first-stage nozzle (110), the second-stage nozzle (13), the third-stage nozzle (15) and the fourth-stage nozzle (16) to be injected into the flame tube (2).
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| CN109595593B (en) * | 2018-11-28 | 2020-06-16 | 西北工业大学 | Swirl combustion chamber head with variable air inlet section |
| CN112066414B (en) * | 2019-06-10 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Combustion chamber, gas turbine and method for suppressing oscillatory combustion |
| CN110440287B (en) * | 2019-07-26 | 2021-04-16 | 中国航发沈阳发动机研究所 | Flow regulating sleeve |
| CN111594872B (en) * | 2020-04-13 | 2021-04-20 | 南京航空航天大学 | Deformable swirler air flow distribution intelligent adjusting system and method |
| CN112709991B (en) * | 2020-12-20 | 2023-09-22 | 青阳县青山生物质能源有限公司 | Environment-friendly straw recycling device |
| CN116255644B (en) * | 2023-02-23 | 2024-08-02 | 中国航发沈阳发动机研究所 | Single-stage swirler adjustable variable geometry combustion chamber |
| CN117628502B (en) * | 2023-11-21 | 2024-08-09 | 扬州市飞鹰电子科技有限公司 | Full premix type honeycomb ceramic burner |
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| JP2950720B2 (en) * | 1994-02-24 | 1999-09-20 | 株式会社東芝 | Gas turbine combustion device and combustion control method therefor |
| DE19512645A1 (en) * | 1995-04-05 | 1996-10-10 | Bmw Rolls Royce Gmbh | Fuel preparation device for gas turbine combustion chamber |
| EP0935095A3 (en) * | 1998-02-09 | 2000-07-19 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| CN100557317C (en) * | 2007-11-29 | 2009-11-04 | 北京航空航天大学 | A kind of aerial engine lean premixed preevaporated low contamination combustion chamber |
| IT1403221B1 (en) * | 2010-12-30 | 2013-10-17 | Nuovo Pignone Spa | PREMIXER OF Vortex COMBUSTION WITH EDWING EDGE AND METHOD |
| US20130284825A1 (en) * | 2012-04-30 | 2013-10-31 | General Electric Company | Fuel nozzle |
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