CN114034061A - Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler - Google Patents
Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler Download PDFInfo
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- CN114034061A CN114034061A CN202111030607.0A CN202111030607A CN114034061A CN 114034061 A CN114034061 A CN 114034061A CN 202111030607 A CN202111030607 A CN 202111030607A CN 114034061 A CN114034061 A CN 114034061A
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- fuel
- nozzle
- swirler
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
Abstract
The invention discloses a liquid fuel nozzle for a dual-fuel combustion chamber of a dual-radial swirler, which comprises an on-duty nozzle, a main-stage spray rod, a front mounting section and a swirler, wherein the front end of the swirler is connected with the front mounting section; a front mounting section is arranged on the front end face of the swirler in the circumferential direction, and a plurality of main-stage spray rods are circumferentially arranged around the front mounting section; the on-duty nozzle is mainly used for supplying fuel to a diffusion combustion flame-stabilizing oil way; the main-stage spray rod is mainly used for supplying liquid fuel and gas fuel for premixed combustion, and the liquid fuel and the gas fuel form good mixing evaporation matching with airflow of the swirler while forming good initial atomization after being sprayed. Through a reasonable structure, the invention can realize high-efficiency stable combustion and reduce NO in a combustion chamber while achieving high-efficiency evaporation and mixing of liquid fuelxAnd (4) discharging, and realizing good consideration of flameout performance and low discharge.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a liquid fuel nozzle for a dual-fuel combustion chamber of a dual-radial-direction swirler.
Background
A dual fuel gas turbine refers to a gas turbine that can use both liquid/gas fuel using dual fuel combustion technology. By implementing the dual-fuel combustion technology in the gas turbine, the adaptability of the gas turbine to fuel can be improved, and the application field of the gas turbine is widened. Therefore, the development of a high-performance dual-fuel gas turbine with better fuel adaptability and the expansion of the application field of the gas turbine become one of the new development directions of the gas turbine.
The dual-fuel combustor is used as a core component of the dual-fuel gas turbine, and needs to have good performance under the condition of combusting liquid and gas fuels, wherein the most important point is to take both the flameout performance and the emission performance into consideration. Because the liquid fuel needs to be atomized and evaporated, the emission performance is generally poorer than that of the liquid fuel when the gas fuel is combusted, and a reasonable nozzle design scheme is required, so that the low emission is well realized and the good ignition and flameout performance is realized when the liquid fuel is combusted.
At present, in a mature dual-fuel gas turbine combustion chamber, nozzles are all in a centrifugal nozzle structure, and diffusion combustion flame is formed by matching with a swirler, so that the problem of considering pollution emission is lacked. Cause NOxThe emission is higher, and basically exceeds more than 150ppm under rated load. Such emissions performance is not satisfactory for current gas turbine related emissions standards.
If the mode of atomizing and premixing combustion of the liquid fuel nozzle is adopted, the problems of lean burn and flameout are more serious because the liquid fuel relates to phase change and evaporation processes, and compared with the premixing combustion of gas fuel, the premixing combustion is relatively difficult to organize, and meanwhile, the premixing combustion is easy to generate oscillatory combustion, so that the nozzle is not feasible to be designed by adopting a pure premixing combustion mode. Under the condition of not carrying out complicated design (such as complicated modes of water injection steam and the like), a more reasonable mode is to arrange a path of diffusion combustion in a combustion chamber, so that the problems of flameout and oscillatory combustion are solved.
In addition, in the design of the premixed combustion oil path, because the existing mature liquid oil path of the dual-fuel combustion chamber generally adopts a centrifugal nozzle (a single oil path or a double oil path), although the initial atomization effect is better than that of a direct-injection nozzle/spray hole, the premixed matching design of the premixed nozzle/spray hole and a swirler is difficult to carry out due to the characteristic of a larger spray cone angle, and the phenomena of ablation, coking, carbon deposition and the like after long-term work, which are easy to cause the aggregation of the spray wall of the fuel liquid drops, are easy to cause faults. Therefore, how to consider the initial atomization effect of the premixed combustion oil nozzle and the matching with the swirler is important and also needed.
Disclosure of Invention
The invention aims to solve the technical problems that the liquid fuel for combustion in a combustion chamber of a dual-fuel gas turbine is high in emission due to diffusion combustion, poor in stability due to premixing combustion and difficult to realize due to the fact that a traditional centrifugal nozzle is premixed and matched with a swirler, and provides a liquid fuel nozzle for a dual-fuel combustion chamber of a dual-radial swirlerxAnd (4) discharging, and realizing good consideration of flameout performance and low discharge.
The technical scheme of the invention is as follows:
a liquid fuel nozzle for a dual-fuel combustion chamber of a dual-radial swirler comprises an on-duty nozzle, a main-stage spray rod, a front mounting section and a swirler, wherein the front end of the swirler is fixedly connected with the front mounting section; a front mounting section is arranged on the front end face of the swirler in the circumferential direction, and a plurality of main-stage spray rods are circumferentially arranged around the front mounting section; the contact surface of the front mounting section and the swirler is a front mounting section cooling wall, and a plurality of cooling holes are uniformly distributed on the front mounting section cooling wall; the main-stage spray rod is provided with a main-stage fuel spray rod and a main-stage gas spray rod, the main-stage fuel spray rod and the main-stage gas spray rod are sequentially arranged along the air flowing direction, and a plurality of main-stage fuel spray rods and main-stage gas spray rods can be included in one air flow path. The main-stage fuel spray rod is used for supplying liquid fuel for premixed combustion, the main-stage fuel spray rod is used for supplying gas fuel for premixed combustion, and the liquid fuel and the gas fuel are sprayed and then form good evaporation and mixing with airflow of the swirler.
The on-duty nozzle comprises a swirl core, a nozzle pipe, an on-duty nozzle cooling cover and an on-duty nozzle rod, wherein the on-duty nozzle rod is arranged at the top of the swirl core, the tail end of the swirl core is sleeved with the nozzle pipe, and the outside of the nozzle pipe is sleeved with the on-duty nozzle cooling cover; the top of the on-duty nozzle rod is an on-duty fuel inlet, the central axial direction of the on-duty nozzle rod is an on-duty fuel flow channel, the tail part of the nozzle pipe is funnel-shaped, and the bottom of the funnel-shaped nozzle pipe is a nozzle.
The cyclone core comprises a cylindrical section and a bottom end head, wherein the top part of the upper end is conical or spherical, the top part and the duty-level nozzle rod form a conical or spherical sealing structure, the middle parts of the top part and the cylindrical section are communicated hollow structures, the bottom part of the cylindrical section is an end surface with a circumferential hole, and the bottom end head of the cylindrical section are in solid connection; the top of the hollow structure is communicated with the duty-level fuel oil flow passage, and the tail of the hollow structure is communicated with the circumferential hole.
The circumferential holes all have the same inclination angle with the central axis of the hollow structure as the center.
The bottom end comprises a connecting rod and an end, the diameter of the connecting rod is obviously smaller than that of the end, and the connecting rod and the end are similar to a screw rod structure with a screw cap; the connecting rod is connected with the cylindrical section, and the end head of the connecting rod is tightly attached to the inner wall surface of the tail part of the nozzle pipe; furthermore, a tangential spiral groove is formed in the outer wall surface of the end head, a fuel swirling groove flow path is formed by the tangential spiral groove and the inner wall surface of the nozzle pipe, and a swirling chamber is formed by the bottom end surface of the cylindrical section, the outer wall surface of the connecting rod and the inner wall surface of the nozzle pipe.
Furthermore, a cavity structure is arranged between the inner wall of the duty-level nozzle cooling cover and the outer wall of the nozzle pipe, the cavity structure serves as a cooling air channel, a cooling cover inflow opening is formed in the side wall, corresponding to the swirl chamber, of the duty-level nozzle cooling cover, and a nozzle cooling hole is formed in the bottom, corresponding to the swirl chamber, of the duty-level nozzle cooling cover.
The axial middle of the main-stage fuel spray rod is provided with a main-stage fuel flow passage, one end of the main-stage fuel flow passage is provided with a fuel inlet, and the other end of the main-stage fuel flow passage is provided with a fuel outlet; the side wall of the main fuel spray rod is provided with a plurality of main fuel spray rod nozzles for main fuel to flow in, and the main fuel spray rod nozzles are communicated with a main fuel flow channel in the middle of the main fuel spray rod.
The axial middle of the main-stage gas spray rod is provided with a main-stage gas flow channel, one end of the main-stage gas spray rod is provided with a gas inlet, and the other end of the main-stage gas spray rod is provided with a gas outlet; the side wall of the main-stage spray rod is provided with a plurality of main-stage gas spray rod nozzles for main-stage gas to flow in, and the main-stage gas spray rod nozzles are communicated with a main-stage gas flow passage in the middle of the main-stage gas spray rod.
The nozzle of the main-stage fuel spray rod is provided with the inclined hole, so that the liquid fuel is sprayed in a direction not perpendicular to the air flow direction but at a certain downstream angle, and the initial momentum of the liquid fuel in the air flow inflow direction is utilized, so that fuel droplets do not collide with the wall in a vane channel of the swirler, and coking and carbon deposition caused by long-time work after fuel adhesion are prevented.
The outer wall surface of the front mounting section is provided with a plurality of fan-shaped sections serving as air inlets of the front mounting section, cooling air is introduced through the air inlets of the front mounting section, the area of the air inlets of the front mounting section is far larger than the effective area of a throttling surface of the cooling air, and the situations of loss or unsmooth flow and the like can be avoided; cooling air is sprayed into a throat of the swirler through cooling holes in the cooling wall of the front mounting section, and the cooling holes adopt an efficient divergent cooling mode with a compound angle, so that the cooling air can be effectively attached to the wall surface of the cooling wall of the mounting section, and the combustion process in the swirler is not affected.
Through the design, the working process of the invention is as follows:
the on-duty fuel oil forms centrifugal conical oil mist through an on-duty nozzle to enter a throat of the swirler, and forms diffusion combustion flame near the central axis of the swirler to be stably combusted; the main fuel is supplied through a main fuel spray rod, spray is generated through spray holes of the main fuel spray rod and enters a swirler vane channel, and the fuel is fully mixed with air flow in the swirler vane channel and evaporated and then enters a swirler throat for combustion;
combustion air enters the combustor through the air inlet of the swirler to participate in combustion; cooling air flows through a cooling hole in the cooling wall of the front mounting section through an air inlet of the front mounting section and enters a swirler to cool the cooling wall of the front mounting section, and meanwhile, part of cooling air flows through a cooling cover inlet on a cooling cover of the on-duty nozzle and is sprayed out through a nozzle cooling hole to cool and thermally protect the on-duty nozzle;
in the class nozzle, fuel oil is supplied from a class fuel oil inlet, the fuel oil flows through the conical top and the cylindrical section of the rotational flow core, then flows out from the circumferential hole at the bottom of the cylindrical section, and then flows through a fuel oil rotational flow groove flow path formed by the tangential spiral groove, so that the fuel oil enters the rotational flow chamber in a rotating manner; fuel oil is subjected to rotary atomization and finally sprayed out in a swirling mode at a spray nozzle to form an oil mist cone required by on-duty diffusion flame; at the moment, the cooling and the nozzle protection are carried out through a cooling air channel between the duty-class nozzle cooling cover and the outer wall surface of the nozzle pipe, and after cooling air enters from an air inlet of the front installation section, a tiny part of the cooling air flows into the nozzle through a cooling cover inflow opening on the duty-class nozzle cooling cover and is sprayed out from a nozzle cooling hole to form a layer of cooling air film protection nozzle; the duty-stage nozzle rod and the rotational flow core are subjected to oil path sealing, and meanwhile, a fuel supply pipeline is prolonged, so that the oil path extends out of the front mounting section of the swirler to be conveniently connected with an external oil supply pipeline;
the main fuel level fuel oil flows in from a main spray rod fuel oil inlet on the main fuel spray rod, and an initial atomized oil mist cone meeting the requirement is obtained by a main fuel spray rod nozzle in a hole pressure atomization mode and is sprayed into a swirler vane channel.
In the present invention, the liquid fuel nozzle has the following two modes of operation:
(1) low load mode of operation
Under the conditions of ignition and small load, only the class nozzle works, the fuel oil only forms centrifugal conical oil mist through the class nozzle to enter a throat of the swirler, and diffusion combustion flame is formed near the central axis of the swirler.
The principle of the small-state working mode is as follows: in view of the fact that the oil supply amount and the air intake amount are small at the moment, the emission standard has no regulation and requirement on the emission in a small state, so the stable process of combustion is mainly considered, a pure diffusion combustion mode is adopted, and good combustion stability is obtained under the working condition of a small state with low pressure and temperature by using the advantages of good stability of diffusion combustion and difficulty in generating combustion oscillation and pressure pulsation. Meanwhile, due to the fact that the small-state oil-gas ratio is low, after all fuel oil is supplied in a centralized mode on duty, a more proper oil-gas ratio can be obtained in a main combustion area for combustion, and the small-state combustion efficiency can be greatly improved and guaranteed.
(2) The large load state working mode:
under the state of high load, a small amount of fuel forms centrifugal conical oil mist from the on-duty nozzle to enter a throat of the swirler, and diffusion combustion flame is formed near the central axis of the swirler; a large amount of fuel generates spray from spray holes on the main-stage fuel spray rod and enters a vane channel of the swirler, and the spray is fully mixed with air flow in the vane channel of the swirler and then enters a throat of the swirler for premixed combustion.
The principle of the working mode in the heavy load state is as follows: the flameout performance of the working condition is guaranteed through the class-wide diffusion flame, a large amount of fuel enters the vane channel of the swirler through the main-stage spray rod, the fuel is guaranteed not to touch the wall in an inclined spraying mode, and meanwhile, the uniformity of the premixed flame is guaranteed through uniform mixing and evaporation with high-temperature air in the vane channel of the swirler; the combustion zone can be ensured to be combusted under a proper equivalence ratio through the mode of division of the fuel oil of the class and the fuel oil of the main grade, and NO is effectively controlledxThereby achieving good pollutant discharge.
The invention has the following beneficial effects:
(1) through reasonable technical measures, the invention solves the technical problems that the liquid fuel for combustion in the combustion chamber of the dual-fuel gas turbine is high in emission by adopting diffusion combustion, poor in stability by adopting premixed combustion and difficult to realize by adopting the premixing matching of the traditional centrifugal nozzle and the swirler, realizes efficient and stable combustion, and reduces NO of the combustion chamberxThe good consideration of flameout performance and low emission is realized;
(2) according to the invention, through a mode that the direct injection type spray holes spray at an angle, the liquid fuel atomization and the premixing of the vortex device are well realized, the high-efficiency evaporation and mixing of a large amount of fuel oil are ensured, the phenomenon that the liquid drops of the fuel oil collide with the wall is also ensured, and the consideration of high-efficiency combustion and coking prevention is ensured;
(3) the invention considers various working conditions in the actual combustion chamber operation, designs two different working modes, can realize the consideration of the high-load working condition and the small-state working condition performance of the combustion chamber, and ensures the high-efficiency and good work of the combustion chamber;
(4) in the invention, the thermal load condition of the head part of the combustion chamber is considered at the same time, a simple and efficient cooling form with multiple inclined holes with compound angle divergence is adopted, and the efficient cooling of the end surface of the nozzle mounting part and the nozzle is realized under the condition of not additionally adding cooling gas;
(5) the invention fully considers the advantages and the defects of two different types of nozzles, namely a centrifugal nozzle and a direct injection type spray orifice, in the liquid fuel gas turbine combustion chamber, fully utilizes the advantages and the defects, and ensures the high-efficiency stable combustion of all combustion working conditions to the maximum extent;
(6) the invention can directly carry out the retrofit design on the biradial natural gas turbine combustion chamber with a mature structure, has simple modification and high realizability, and can effectively save the investment compared with the newly developed dual-fuel combustion chamber.
Drawings
Fig. 1 is a schematic front view of the present invention.
Fig. 2 is a left side view structural diagram of the present invention.
Fig. 3 is a right-view structural diagram of the present invention.
Fig. 4 is a schematic front sectional view of the present invention.
FIG. 5 is a schematic view of the on-duty nozzle of the present invention.
Fig. 6 is a schematic view of the cross-sectional structure a-a of fig. 5.
FIG. 7 is a schematic view of the bottom nozzle cooling hole of the duty nozzle cooling shroud of the present invention.
Fig. 8 is a schematic front view of the liquid fuel primary spray bar of the present invention.
Fig. 9 is a left side view schematic of the liquid fuel primary spray bar of the present invention.
FIG. 10 is a schematic view of the liquid fuel main stage of the present invention in conjunction with a swirler.
FIG. 11 is a schematic view of the structure B-B of FIG. 10.
Fig. 12 is a schematic view of the structure C-C of fig. 11.
FIG. 13 is a schematic structural view of a front mounting segment stave of the present invention.
Fig. 14 is a side view of the structure of fig. 13.
Fig. 15 is a schematic view of the structure D-D of fig. 13.
Fig. 16 is a schematic view of the structure E-E of fig. 14.
Fig. 17 is a schematic structural view of the swirling core of the present invention.
Fig. 18 is a schematic cross-sectional view of fig. 17.
Wherein the drawings are compared: 1 duty level nozzle, 2 main level spray rod, 3 front installation section, 4 vortex device, 11 swirl core, 12 spout pipe, 13 duty level nozzle cooling cover, 14 duty level nozzle rod, 111 duty level fuel inlet, 112 circumferential hole, 113 swirl chamber, 114 spout, 115 nozzle cooling hole, 116 cooling cover inlet, 117 tangential spiral groove, 211 main level fuel spray rod inlet, 212 main level fuel spray rod spout, 31 front installation section front section, 32 front installation section cooling wall, 311 front installation section air inlet, 312 cooling hole, 41 vortex device blade channel, 42 vortex device throat, 411 vortex device air inlet.
Detailed Description
Example 1
As shown in fig. 1-4, a liquid fuel nozzle for a dual-fuel combustion chamber of a dual-radial swirler comprises an on-duty nozzle 1, a main-stage spray rod 2, a front mounting section 3 and a swirler 4, wherein the above components are assembled into a whole to jointly finish the atomization and evaporation of head fuel oil of the combustion chamber.
Specifically, the front mounting section 3 comprises a front mounting section front section 31 and a rear section, the front end of the swirler 4 is fixedly connected with the rear section of the front mounting section 3, the duty-level nozzle 1 is mounted on the central axis of the front mounting section 3, and the duty-level nozzle 1 is communicated to the swirler throat 42; a plurality of main-stage spray rods 2 are circumferentially arranged on the front end face of the swirler 4 by taking the front mounting section 3 as the center, and spray holes of the main-stage spray rods 2 are communicated to a swirler vane channel 41; the contact surface of the front mounting section 3 and the swirler 4 is a front mounting section cooling wall 32, and a plurality of cooling holes 312 are uniformly distributed on the front mounting section cooling wall 32; the value class nozzle 1 is mainly used for supplying fuel oil to a diffusion combustion flame-stabilizing oil way; the main-stage spray rod 2 is provided with a main-stage fuel oil spray rod and a main-stage gas spray rod, the main-stage fuel oil spray rod and the main-stage gas spray rod are sequentially arranged along the air flowing direction, and a plurality of main-stage fuel oil spray rods and main-stage gas spray rods can be included in one air flow path.
The main fuel spray rod is used for supplying liquid fuel for premixed combustion, the main fuel spray rod is used for supplying gas fuel for premixed combustion, and the liquid fuel and the gas fuel form good initial atomization after being sprayed and simultaneously form good evaporation mixing with airflow of the swirler 4.
The liquid fuel nozzle operates as follows: the on-duty fuel oil forms centrifugal conical oil mist through the on-duty nozzle 1 and enters the swirler throat 42, and diffusion combustion flame is formed near the central axis of the swirler 4 to be stably combusted; the main fuel is supplied through a main fuel spray rod, and spray generated by a main fuel spray rod nozzle 212 on the main fuel spray rod enters a swirler vane channel 41, is fully mixed with air flow in the swirler vane channel 41 and is evaporated and then enters a swirler throat 42 for combustion; combustion air enters through swirler air inlet 411 to participate in combustion; the cooling air flows through the cooling holes 312 on the front mounting section cooling wall 32 through the front mounting section air inlet 311 and enters the swirler 4 to cool the front mounting section cooling wall 32, and meanwhile, part of the cooling air flows through the cooling cover inlet 116 on the on-duty nozzle cooling cover 13 and is sprayed out through the nozzle cooling holes 115 to cool and thermally protect the on-duty nozzle 1.
Example 2
As shown in fig. 5-7, based on embodiment 1, the on-duty nozzle 1 includes a swirl core 11, a nozzle tube 12, an on-duty nozzle cooling cover 13, and an on-duty nozzle rod 14, where the on-duty nozzle rod 14 is installed at the top of the swirl core 11, the nozzle tube 12 is sleeved at the tail end of the swirl core 11, and the on-duty nozzle cooling cover 13 is sleeved outside the nozzle tube 12; the top of the on-duty nozzle rod 14 is an on-duty fuel inlet 111, the central axial direction of the on-duty nozzle rod 14 is an on-duty fuel flow passage, the tail part of the spout pipe 12 is funnel-shaped, and the bottom of the funnel-shaped is a spout 114.
The cyclone core 11 comprises a cylindrical section and a bottom end head, wherein the top part of the upper end is a conical or spherical surface, the top part and the duty-level nozzle rod 14 form a conical or spherical sealing structure, the middle parts of the top part and the cylindrical section are communicated hollow structures, the bottom part of the cylindrical section is an end surface with a circumferential hole 112, and the bottom end surface and the bottom end head of the cylindrical section are in solid connection; the top of the hollow structure is communicated with the duty-level fuel oil flow passage, and the tail of the hollow structure is communicated with the circumferential hole 112.
The circumferential holes 112 all have the same inclination angle centered on the central axis of the hollow structure.
The bottom end comprises a connecting rod and an end, the diameter of the connecting rod is obviously smaller than that of the end, and the connecting rod and the end are similar to a screw rod structure with a screw cap; the connecting rod is connected with the cylindrical section, and the end head of the connecting rod is tightly attached to the inner wall surface of the tail part of the nozzle pipe 12; furthermore, a tangential spiral groove 117 is formed in the outer wall surface of the end head, a fuel swirling groove flow path is formed by the tangential spiral groove 117 and the inner wall surface of the spout pipe 12, and a swirling chamber 113 is formed by the bottom end surface of the cylindrical section, the outer wall surface of the connecting rod and the inner wall surface of the spout pipe 12.
The swirl core 11 mainly functions to form a ball cone seal with the on-duty nozzle rod 14, fuel is introduced from the on-duty fuel inlet 111, and then the fuel flows through the circumferential hole 1122 and then flows through the tangential spiral groove 117 to enter the swirl chamber 113 formed by the front end wall surface of the swirl core 11 and the inner wall surface of the nozzle. After the fuel is subjected to rotary atomization, the fuel is finally sprayed out in a swirling mode at the nozzle 114 to form an oil mist cone required by a class diffusion flame.
A cavity structure is arranged between the inner wall of the duty-level nozzle cooling cover 13 and the outer wall of the nozzle pipe 12, the cavity structure is used as a cooling air channel, a cooling cover inlet 116 is arranged on the side wall of the duty-level nozzle cooling cover 13 corresponding to the swirl chamber 113, and a nozzle cooling hole 115 is arranged at the bottom of the duty-level nozzle cooling cover 13 corresponding to the swirl chamber 113. The duty-stage nozzle rod 14 mainly has the functions of sealing an oil path with the swirl core 11 and prolonging a fuel supply pipeline, so that the oil path extends out of the swirler 4 and the front mounting section 3 to be connected with an external oil supply pipeline.
Example 3
As shown in fig. 8-9, on the basis of embodiment 1 or 2, the axial middle of the main-stage fuel spray rod is a main-stage fuel flow passage, one end of the main-stage fuel flow passage is a main-stage spray rod fuel inlet 211, and the other end of the main-stage fuel flow passage is a main-stage spray rod fuel outlet; the side wall of the main fuel spray rod is provided with a plurality of main fuel spray rod nozzles 212 for the inflow of main fuel, and the main fuel spray rod nozzles 212 are communicated with a main fuel flow passage in the middle of the main fuel spray rod 2.
The main fuel grade fuel oil flows in from a main fuel spray rod fuel oil inlet 211 on the main fuel spray rod, and an initial atomized oil mist cone meeting the requirement is obtained by a main fuel spray rod nozzle 212 in a simple hole pressure atomization mode and is sprayed into a swirler vane channel 41.
The main combustion stage fuel oil and the swirler 4 are matched as shown in fig. 10-12, the main combustion stage fuel oil spray rod nozzle 212 is provided with an inclined hole structure, so that the fuel oil injection direction and the air flow direction do not enter vertically, but have a certain forward flow angle, and the fuel oil droplets do not collide with the wall in the swirler vane channel 41 by utilizing the initial momentum of the fuel oil in the air flow inflow direction, so that the long-time operation coking and carbon deposition after the fuel oil is attached can be prevented.
Example 4
As shown in fig. 13 to 16, in any of embodiments 1 to 3, the front mounting section 3 has a plurality of fan-shaped sections as air inlets 311 on the outer wall surface thereof.
In this embodiment, three segments are provided through which cooling air is introduced. Thus, the design area of the air inlet 311 of the front mounting section is far larger than the effective area of the throttling surface of the cooling air, and the situations of loss or unsmooth flow and the like can not be caused. The cooling air is sprayed into the throat 42 of the swirler through the cooling holes 312 on the front mounting section cooling wall 32, and the cooling holes 312 adopt an efficient divergent cooling mode with a compound angle, so that the cooling air can be effectively attached to the wall surface of the front mounting section cooling wall 32, and the combustion process in the swirler 4 is not affected.
Through the design, the working process of the invention is as follows:
the on-duty fuel oil forms centrifugal conical oil mist through the on-duty nozzle 1 and enters the swirler throat 42, and diffusion combustion flame is formed near the central axis of the swirler 4 to be stably combusted; the main-grade fuel oil is supplied through the main-grade spray rod 2, generates spray through spray holes of the main-grade spray rod 2, enters the swirler vane channel 41, is fully mixed with air flow in the swirler vane channel 41, is evaporated and then enters the swirler throat 42 for combustion;
combustion air enters through swirler air inlet 411 to participate in combustion; cooling air flows through a cooling hole 312 on the front mounting section cooling wall 32 through a front mounting section air inlet 311 and enters the swirler 4 to cool the front mounting section cooling wall 32, and meanwhile, part of the cooling air flows into a cooling cover inlet 116 on the duty-level nozzle cooling cover 13 and is sprayed out through the nozzle cooling hole 115 to cool and thermally protect the nozzle 1;
in the class nozzle 1, fuel oil is introduced from a class fuel oil inlet 111 and flows through the top of the swirl core 11 and the cylindrical section, then flows out from a circumferential hole 112 at the bottom of the cylindrical section, and then flows through a fuel oil swirl groove flow path formed by the tangential spiral groove 117, so that the fuel oil is rotated to enter the swirl chamber 113; fuel oil is subjected to rotary atomization and finally sprayed out in a swirling mode at a spray nozzle to form an oil mist cone required by on-duty diffusion flame; at this time, the cooling air enters from the air inlet 311 of the front installation section, and then a small part of the cooling air flows into the nozzle through the cooling cover inflow port 116 on the cooling cover 13 of the on-duty nozzle and is sprayed out from the nozzle cooling hole 115 to form a layer of cooling air film protection nozzle; the class nozzle rod 14 and the rotational flow core 11 are sealed in an oil way, and meanwhile, a fuel supply pipeline is prolonged, so that the oil way extends out of the swirler 4 and the front mounting section 3 to be connected with an external oil supply pipeline;
the main fuel grade fuel oil flows in from a main fuel spray rod fuel oil inlet 211 on the main fuel spray rod, and an initial atomized oil mist cone meeting the requirement is obtained by a main fuel spray rod nozzle 212 in a hole pressure atomization mode and is sprayed into a swirler vane channel 41.
The liquid fuel nozzle of the present invention has the following two modes of operation:
(1) low load mode of operation
In the ignition and small load state, only the class nozzle 1 works, the fuel oil forms centrifugal conical oil mist only through the class nozzle 1 and enters the swirler throat 42, and diffusion combustion flame is formed near the central axis of the swirler 4.
The principle of the working mode in the small load state is as follows: in view of the fact that the oil supply amount and the air intake amount are small at the moment, the emission standard has no regulation and requirement on the emission in a small state, so the stable process of combustion is mainly considered, a pure diffusion combustion mode is adopted, and good combustion stability is obtained under the working condition of a small state with low pressure and temperature by using the advantages of good stability of diffusion combustion and difficulty in generating combustion oscillation and pressure pulsation. Meanwhile, due to the fact that the small-state oil-gas ratio is low, after all fuel oil is supplied in a centralized mode on duty, a more proper oil-gas ratio can be obtained in a main combustion area for combustion, and the small-state combustion efficiency can be greatly improved and guaranteed.
(2) The large load state working mode:
under the state of high load, a small amount of fuel forms centrifugal conical oil mist from the on-duty nozzle 1 and enters the swirler throat 42, and diffusion combustion flame is formed near the central axis of the swirler 4; a large amount of fuel generates spray from a main-stage fuel spray rod nozzle 212 on the main-stage fuel spray rod, enters the swirler vane channel 41, is fully mixed with air flow in the swirler vane channel 41 and evaporates, and then enters the swirler throat 42 for premixed combustion.
The principle of the working mode in the heavy load state is as follows: the flameout performance of the working condition is guaranteed through the class-wide diffusion flame, a large amount of fuel enters the swirler vane channel 41 through the main-stage spray rod 2, the fuel is guaranteed not to touch the wall in an inclined spraying mode, and meanwhile, the uniformity of the premixed flame is guaranteed through uniform mixing and evaporation with high-temperature air in the swirler vane channel 41; the combustion zone can be ensured to be combusted under a proper equivalence ratio through the form of division of the class fuel and the main fuel, the generation of NOx is effectively controlled, and therefore good pollution emission is achieved.
Claims (11)
1. A liquid fuel nozzle for a dual radial swirler dual fuel combustor, characterized by: the spray gun comprises an on-duty nozzle (1), a main spray rod (2), a front mounting section (3) and a swirler (4), wherein the front end of the swirler (4) is fixedly connected with the front mounting section (3), the on-duty nozzle (1) is mounted on the central axis of the front mounting section (3), and the on-duty nozzle (1) is communicated to a swirler throat (42); a front mounting section (3) is arranged on the front end face of the swirler (4) in the circumferential direction as the center, and a plurality of main-stage spray rods (2) are circumferentially arranged, and spray holes of the main-stage spray rods (2) are communicated to swirler vane channels (41); the contact surface of the front mounting section (3) and the swirler (4) is a front mounting section cooling wall (32), and a plurality of cooling holes (312) are uniformly distributed on the front mounting section cooling wall (32); the on-duty nozzle (1) is used for supplying fuel to a diffusion combustion flame-stabilizing oil way; the main-stage spray rod (2) is provided with a main-stage fuel spray rod and a main-stage gas spray rod, the main-stage fuel spray rod is used for supplying liquid fuel for premixed combustion, the main-stage gas spray rod is used for supplying gas fuel for premixed combustion, and the liquid fuel and the gas fuel are sprayed and then form evaporation mixing with airflow of the swirler (4).
2. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 1, wherein: the on-duty nozzle (1) comprises a swirl core (11), a nozzle pipe (12), an on-duty nozzle cooling cover (13) and an on-duty nozzle rod (14), wherein the on-duty nozzle rod (14) is arranged at the top of the swirl core (11), the nozzle pipe (12) is sleeved at the tail end of the swirl core (11), and the on-duty nozzle cooling cover (13) is sleeved outside the nozzle pipe (12); the top of the on-duty nozzle rod (14) is an on-duty fuel inlet (111), the central axial direction of the on-duty nozzle rod (14) is an on-duty fuel flow channel, the tail part of the nozzle pipe (12) is funnel-shaped, and the funnel-shaped bottom is a nozzle (114).
3. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 2, wherein: the cyclone core (11) comprises a cylindrical section and a bottom end head, wherein the top part of the upper end is a conical or spherical surface, the top part and the duty-level nozzle rod (14) form a conical or spherical sealing structure, the middle parts of the top part and the cylindrical section are communicated hollow structures, the bottom part of the cylindrical section is an end surface with a circumferential hole (112), and the bottom end surface of the cylindrical section is in solid connection with the bottom end head; the top of the hollow structure is communicated with the duty-level fuel oil flow passage, and the tail of the hollow structure is communicated with the circumferential hole (112); the circumferential holes (112) all have the same inclination angle by taking the central axis of the hollow structure as the center.
4. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 3, wherein: the bottom end comprises a connecting rod and an end, and the diameter of the connecting rod is smaller than that of the end; the connecting rod is connected with the cylindrical section, and the end head of the connecting rod is tightly attached to the inner wall surface of the tail part of the nozzle pipe (12).
5. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 3 or 4, wherein: the outer wall surface of the end head is provided with a tangential spiral groove (117), the tangential spiral groove (117) and the inner wall surface of the nozzle pipe (12) form a fuel swirl groove flow path, and the bottom end surface of the cylindrical section, the outer wall surface of the connecting rod and the inner wall surface of the nozzle pipe (12) form a swirl chamber (113).
6. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 2, wherein: a cavity structure is arranged between the inner wall of the duty nozzle cooling cover (13) and the outer wall of the nozzle pipe (12), the cavity structure is used as a cooling air channel, a cooling cover inflow opening (116) is formed in the side wall, corresponding to the swirling flow chamber (113), of the duty nozzle cooling cover (13), and a nozzle cooling hole (115) is formed in the bottom, corresponding to the swirling flow chamber (113), of the duty nozzle cooling cover (13).
7. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 1, wherein: the axial middle of the main fuel spray rod is provided with a main fuel oil flow passage, one end of the main fuel oil flow passage is provided with a main spray rod fuel oil inlet (211), and the other end of the main fuel oil flow passage is provided with a main spray rod fuel oil outlet; the side wall of the main fuel spray rod is provided with a plurality of main fuel spray rod nozzles (212) for main fuel to flow in, and the main fuel spray rod nozzles (212) are communicated with a main fuel flow passage in the middle of the main fuel spray rod.
8. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 7, wherein: the main-stage fuel spray rod nozzle (212) is of an inclined hole structure, so that a certain forward flow angle is formed between the liquid fuel injection direction and the air flow direction.
9. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 1, wherein: a plurality of fan-shaped sections serving as air inlets (311) of the front mounting section are formed in the outer wall surface of the front mounting section, cooling air is introduced through the air inlets (311) of the front mounting section, and the area of the air inlets (311) of the front mounting section is larger than that of a cooling air throttling surface; cooling air is injected into the swirler throat (42) through cooling holes (312) in the front mounting section stave (32) such that the cooling air adheres to the wall surfaces of the mounting section stave (32).
10. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 1, wherein the liquid fuel nozzle operates as follows:
the on-duty fuel oil forms centrifugal conical oil mist through the on-duty nozzle (1) and enters a swirler throat (42), and diffusion combustion flame stable combustion is formed near the central axis of the swirler (4); the main fuel is supplied through a main fuel spray rod, spray generated through spray holes of the main fuel spray rod enters a vortex device blade channel (41), is fully mixed with air flow in the vortex device blade channel (41) and is evaporated, and then enters a vortex device throat (42) for combustion;
combustion air enters through a swirler air inlet (411) to participate in combustion; cooling air flows through a cooling hole (312) on a cooling wall (32) of the front mounting section through an air inlet (311) of the front mounting section and enters a swirler (4) to cool the cooling wall (32) of the front mounting section, and meanwhile, part of cooling air flows into a cooling cover inflow hole (116) on a nozzle cooling cover (13) on duty and is sprayed out through a nozzle cooling hole (115) to cool and thermally protect a nozzle (1) on duty;
in the class nozzle (1), fuel oil is introduced from a class fuel oil inlet (111) and flows through the top of the rotational flow core (11) and the cylindrical section, then flows out from a circumferential hole (112) at the bottom of the cylindrical section, and then flows through a fuel oil rotational flow groove flow path formed by a tangential spiral groove (117) to enable the fuel oil to enter the rotational flow chamber (113) in a rotating way; fuel oil is subjected to rotary atomization and finally sprayed out in a swirling mode at a spray nozzle to form an oil mist cone required by on-duty diffusion flame; after cooling air enters from an air inlet (311) of the front mounting section, a tiny part of cooling air flows into the nozzle through a cooling cover inflow port (116) on the cooling cover (13) of the class nozzle and is sprayed out from a nozzle cooling hole (115) to form a layer of cooling air film protection nozzle; the on-duty nozzle rod (14) and the swirl core (11) are sealed in an oil way, and meanwhile, a fuel supply pipeline is prolonged, so that the oil way extends out of the swirler (4) and the front mounting section (3) and is connected with an external oil supply pipeline;
the main fuel grade fuel oil flows in from a main spray rod fuel oil inlet (211) on the main fuel grade spray rod, and an initial atomized oil mist cone meeting the requirement is obtained by a main fuel grade spray rod nozzle (212) in a hole pressure atomization mode and is sprayed into a swirler vane channel (41).
11. The liquid fuel nozzle for a dual radial swirler dual fuel combustor as claimed in claim 1, wherein the liquid fuel nozzle has two modes of operation:
(1) the working mode in a small load state is as follows: in the ignition and small load state, only the duty nozzle (1) works, the fuel oil forms centrifugal conical oil mist only through the duty nozzle (1) and enters a swirler throat (42), and diffusion combustion flame is formed near the central axis of the swirler (4);
(2) the large load state working mode: under the state of high load, a small amount of fuel forms centrifugal conical oil mist from the duty nozzle (1) and enters a swirler throat (42), and diffusion combustion flame is formed near the central axis of the swirler (4); a large amount of fuel generates spray from spray holes on a main-stage fuel spray rod and enters a swirler vane channel (41), and the spray mist is fully mixed with air flow in the swirler vane channel (41) and evaporated and then enters a swirler throat (42) for premixed combustion.
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| CN202111030607.0A CN114034061B (en) | 2021-09-03 | 2021-09-03 | Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler |
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| CN202111030607.0A CN114034061B (en) | 2021-09-03 | 2021-09-03 | Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler |
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