CN114034061B - 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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- CN114034061B CN114034061B CN202111030607.0A CN202111030607A CN114034061B CN 114034061 B CN114034061 B CN 114034061B CN 202111030607 A CN202111030607 A CN 202111030607A CN 114034061 B CN114034061 B CN 114034061B
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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
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- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Spray-Type Burners (AREA)
Abstract
The invention discloses a double-radial vortex deviceThe liquid fuel nozzle of the fuel combustion chamber comprises a class 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 plurality of main-stage spray bars are circumferentially arranged on the front end surface of the swirler by taking the front mounting section as the center, and spray holes of the main-stage spray bars are communicated to a swirler blade channel; the duty nozzle is mainly used for fuel oil supply of 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 the air flow of the swirler while forming good initial atomization after being injected. The invention has reasonable structure, can realize high-efficiency stable combustion and reduce NO in the combustion chamber while achieving high-efficiency evaporation and blending of liquid fuel x And emission, and good compromise of flameout performance and low emission is realized.
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 swirler.
Background
A dual fuel gas turbine refers to a gas turbine that utilizes dual fuel combustion technology and can use liquid/gas fuels simultaneously. 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 can be widened. Therefore, the development of a high-performance dual-fuel gas turbine with higher fuel adaptability expands the application field of the gas turbine and becomes one of the new development directions of the gas turbine.
The dual-fuel combustion chamber is used as a core component of the dual-fuel gas turbine, and has good performance under the condition of burning liquid and gas fuel, wherein the most important point is the combination of the on-off performance and the emission performance. 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 burnt, and a reasonable nozzle design scheme is required, so that the liquid fuel is burnt, low emission is well realized, and meanwhile, the liquid fuel has good flameout performance.
At present, a more mature dual-fuel gas turbine combustion chamber adopts a centrifugal nozzle structure, and a diffusion combustion flame is formed by matching a swirler, so that the problem of pollution emission is solved. Causing NO x The emission is high, and the emission is basically more than 150ppm under rated load. Such emissions performance is not satisfactory for current gas turbine related emissions standards.
If the liquid fuel nozzle is adopted for atomization and premixed combustion, the liquid fuel is relatively difficult to organize compared with the premixed combustion of the gas fuel because of the phase change and evaporation processes, the problem of lean combustion flameout is more serious, and meanwhile, the premixed combustion is easy to generate oscillation combustion, so that the nozzle is not feasible to design by adopting a pure premixed combustion mode. Under the condition of not carrying out complex design (such as complex modes of water vapor injection and the like), a reasonable mode is to arrange one-way diffusion combustion in the combustion chamber, so that the problems of flameout and oscillation combustion are solved.
In addition, in the design of the premixed combustion oil way, as the existing mature liquid oil way of the dual-fuel combustion chamber generally adopts a centrifugal nozzle (a single oil way or a double oil way), the initial atomization effect is better than that of a direct injection nozzle/spray hole, but the premixed combustion oil way is difficult to be matched with a swirler due to the characteristic of larger spray cone angle, and the phenomenon of ablation, coking, carbon deposition and the like after long-term working is extremely easy to cause the aggregation of fuel liquid drop spray walls, so that faults are caused. Therefore, it is important to consider the initial atomization effect of the premixed combustion oil path nozzle and the matching with the swirler.
Disclosure of Invention
The invention aims at solving the technical problems that the liquid fuel for combustion in the combustion chamber of the dual-fuel gas turbine has higher diffusion combustion emission, poor premixed combustion stability and difficult realization of premixed matching between the traditional centrifugal nozzle and a swirlerThe liquid fuel nozzle for the dual-fuel combustion chamber of the double-radial swirler is provided, and through reasonable structural design, high-efficiency stable combustion can be realized while high-efficiency evaporation and blending of liquid fuel are achieved, and NO in the combustion chamber is reduced x And emission, and good compromise of flameout performance and low emission is realized.
The technical scheme of the invention is as follows:
the liquid fuel nozzle for the dual-fuel combustion chamber of the double-radial swirler comprises a shift 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 plurality of main-stage spray bars are circumferentially arranged on the front end surface of the swirler by taking the front mounting section as the center, and spray holes of the main-stage spray bars are communicated to a swirler blade channel; the contact surface of the front mounting section and the vortex device 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 flow direction, and one air flow path can comprise a plurality of main-stage fuel spray rods and main-stage gas spray rods. The main-stage fuel spray rod is used for supplying liquid fuel for premixed combustion, and the main-stage fuel spray rod is used for supplying gas fuel for premixed combustion, and the liquid fuel and the gas fuel are well vaporized and mixed with the air flow of the swirler after being injected.
The on-duty nozzle comprises a cyclone 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 cyclone core, the nozzle pipe is sleeved at the tail end of the cyclone core, and the on-duty nozzle cooling cover is sleeved outside the nozzle pipe; 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 passage, the tail of the nozzle pipe is funnel-shaped, and the bottom of the funnel is a nozzle.
The cyclone core comprises an upper end top, a middle cylindrical section and a bottom end head, wherein the top is conical or spherical, the top and the duty nozzle rod form a conical or spherical sealing structure, the middle of the top and the cylindrical section is a communicated hollow structure, the bottom of the cylindrical section is an end face of a Zhou Xiangkong belt, and the end face of the bottom of the cylindrical section is in solid connection with the bottom end head; the top of the hollow structure is communicated with the duty grade fuel 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 head comprises a connecting rod and an end head, the diameter of the connecting rod is obviously smaller than that of the end head, and the connecting rod and the end head are similar to a screw structure with a screw cap; the connecting rod is connected with the cylindrical section, and the end head is clung to the inner wall surface of the tail part of the nozzle pipe; further, a tangential spiral groove is formed in the outer wall surface of the end head, a fuel oil rotational flow groove flow path is formed in the tangential spiral groove and the inner wall surface of the nozzle pipe, and a rotational flow chamber is formed in 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 nozzle cooling cover and the outer wall of the nozzle pipe, the cavity structure is used as a cooling air channel, a cooling cover inflow port is arranged on the side wall of the duty nozzle cooling cover corresponding to the cyclone chamber, and a nozzle cooling hole is arranged at the bottom of the duty nozzle cooling cover corresponding to the cyclone chamber.
The axial middle of the main-stage fuel spray rod is provided with a main-stage fuel flow channel, one end of the main-stage fuel flow channel is provided with a fuel inlet, and the other end of the main-stage fuel flow channel is provided with a fuel outlet; the side wall of the main-stage fuel spray rod is provided with a plurality of main-stage fuel spray rod nozzles used for flowing in main-stage fuel, and the main-stage fuel spray rod nozzles are communicated with a main-stage fuel flow passage in the middle of the main-stage 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 flow channel 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 used for flowing in main-stage gas, and the main-stage gas spray rod nozzles are communicated with a main-stage gas flow channel in the middle of the main-stage gas spray rod.
Through adopting the structure of opening the inclined hole to the main-stage fuel spray boom nozzle, the liquid fuel injection direction and the air flow direction do not vertically enter, but have a certain forward flow angle, and the initial momentum of the liquid fuel in the air flow inflow direction is utilized, so that fuel drops do not collide with walls in the swirler vane channel, thereby preventing long-time working coking and carbon deposition after fuel adhesion.
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 the cooling air throttling surface, and the conditions of loss, unsmooth flow and the like are avoided; cooling air is sprayed into the throat of the swirler through cooling holes on the cooling wall of the front mounting section, and the cooling holes adopt an efficient mode with compound angle divergent cooling, 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 influenced.
Through the design, the working process of the invention is as follows:
the valve class fuel oil forms centrifugal conical oil mist to enter a throat of the vortex device through a valve class nozzle, and diffusion combustion flame is formed near the central axis of the vortex device to stably burn; the main grade fuel is supplied through a main grade fuel spray rod, spray generated through spray holes of the main grade fuel spray rod enters a vortex blade channel, and enters a vortex throat for combustion after being fully mixed and evaporated with air flow in the vortex blade channel;
combustion air enters through the air inlet of the swirler to participate in combustion; cooling air flows through cooling holes in the cooling wall of the front mounting section through an air inlet of the front mounting section to enter the vortex device to cool the cooling wall of the front mounting section, and meanwhile, part of cooling air flows into the cooling cover inlet on the duty nozzle cooling cover through the cooling cover inlet on the duty nozzle cooling cover and is sprayed out through the nozzle cooling holes to cool and thermally protect the duty nozzle;
in the class nozzle, fuel is led in and supplied from a class fuel inlet, flows through the conical top part and the cylindrical section of the cyclone core, flows out from the circumferential hole at the bottom of the cylindrical section, and flows through a fuel cyclone channel flow path formed by tangential spiral channels, so that the fuel rotates to enter the cyclone chamber; after rotary atomization, the fuel is finally sprayed out by rotational flow at a nozzle to form an oil mist cone required by class diffusion flame; at the moment, cooling and protecting the nozzle safety through a cooling air channel between the shift-stage nozzle cooling cover and the outer wall surface of the nozzle pipe, wherein after cooling air enters from an air inlet of the front mounting section, a very small part of cooling air flows into the nozzle through a cooling cover inlet on the shift-stage nozzle cooling cover and is sprayed out from a nozzle cooling hole to form a layer of cooling air film protecting nozzle; the class nozzle rod and the swirl core are subjected to oil way sealing, and meanwhile, the fuel supply pipeline is prolonged, so that the oil way extends out of the front installation section of the swirler to be connected with an external fuel supply pipeline;
the primary fuel flows in from a primary spray rod fuel inlet on the primary fuel spray rod, and an initial atomized oil mist cone meeting the requirements is obtained by adopting a hole pressure atomization mode through a primary fuel spray rod nozzle and is sprayed into a vortex blade channel.
In the present invention, the liquid fuel nozzle has the following two modes of operation:
(1) Small load state operation mode
Under the ignition and small load state, only the valve class nozzle works, fuel oil only forms centrifugal conical oil mist through the valve class nozzle to enter the 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 fuel supply amount and the air inflow are smaller at this time, the emission standard does not prescribe or require the emission in a small state, so that the stable process of combustion is mainly considered, a pure diffusion combustion mode is adopted, the advantages of good diffusion combustion stability and difficulty in generating combustion oscillation and pressure pulsation are utilized, and good combustion stability is obtained under the working conditions of a small state with lower pressure and temperature. Meanwhile, because the small-state oil gas is relatively low, after all the fuel oil is concentrated on the duty level for supply, the fuel oil can be combusted in a main combustion area by obtaining more proper oil gas ratio, and the combustion efficiency of the small state can be greatly improved and ensured.
(2) Large load state operation mode:
in a state of higher load, a small amount of fuel forms centrifugal conical oil mist from the duty nozzle to enter the throat of the swirler, and forms diffusion combustion flame near the central axis of the swirler; a large amount of fuel oil is sprayed from spray holes on a main-stage fuel oil spray rod to enter a vortex blade channel, and enters a vortex throat for premixed combustion after being fully mixed and evaporated with air flow in the vortex blade channel.
The principle of the working mode in the heavy load state is as follows: the flameout performance of the working condition is ensured through the class diffusion flame, a large amount of fuel enters the swirler vane passage through the main-stage spray rod, the fuel is ensured not to collide with the wall by adopting an inclined spraying mode, and meanwhile, the uniformity of the premixed flame is ensured through the uniform mixing and evaporation of the fuel and high-temperature air in the swirler vane passage; the combustion areas can be ensured to burn under proper equivalent ratio by the forms of value class and main grade fuel oil partition, thereby effectively controlling NO x Thereby achieving good pollutant emissions.
The beneficial effects of the invention are as follows:
(1) The invention solves the technical problems that the liquid fuel for combustion in the combustion chamber of the dual-fuel gas turbine adopts diffusion combustion to discharge higher, adopts premixing combustion to realize poor stability and adopts the traditional centrifugal nozzle to realize premixing matching with the swirler by reasonable technical measures, realizes high-efficiency stable combustion and reduces NO in the combustion chamber x Emission, the flameout performance and low emission are well considered;
(2) According to the invention, through the mode of angular injection of the direct injection spray holes, the premixing matching of liquid fuel atomization and the swirler is well realized, a large amount of fuel is guaranteed to be efficiently evaporated and mixed, the phenomenon that fuel drops collide with walls is avoided, and the high-efficiency combustion and coking prevention are guaranteed;
(3) According to the invention, various working conditions in the actual combustion chamber operation are considered, two different working modes are designed, the high-load working condition and the small-state working condition of the combustion chamber can be considered, and the high-efficiency and good working of the combustion chamber is ensured;
(4) According to the invention, the heat load condition of the head of the combustion chamber is considered, and a simple and efficient cooling mode with a composite angle-divergent multi-inclined hole is adopted, so that the end face of the nozzle mounting position and the nozzle are efficiently cooled under the condition that no additional cooling gas is needed;
(5) The invention fully considers the advantages and the disadvantages of two different types of nozzles, namely a centrifugal nozzle and a direct injection nozzle in the combustion chamber of the liquid fuel gas turbine, fully utilizes the advantages and the disadvantages, and ensures the high-efficiency stable combustion of all combustion working conditions to the greatest extent;
(6) The invention can directly carry out retrofit design on the double-radial natural gas turbine combustion chamber with a mature structure, has simple reformation and high realizability, and can effectively save investment compared with a newly-developed double-fuel combustion chamber.
Drawings
Fig. 1 is a schematic diagram of a front view structure of the present invention.
Fig. 2 is a schematic left-view structure of the present invention.
Fig. 3 is a right-side view of the present invention.
Fig. 4 is a schematic view of a front view in cross section.
Fig. 5 is a schematic diagram of the front view of the 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 structure of the nozzle cooling holes at the bottom of the duty nozzle cooling cover of the present invention.
Fig. 8 is a schematic view showing a front view of a liquid fuel primary boom according to the present invention.
Fig. 9 is a schematic left-hand view of the liquid fuel primary boom of the present invention.
FIG. 10 is a schematic illustration of the cooperation of the liquid fuel main stage and swirler of the present invention.
Fig. 11 is a schematic diagram of the B-B structure of fig. 10.
Fig. 12 is a schematic view of the C-C structure of fig. 11.
FIG. 13 is a schematic view of the structure of the stave of the present invention at the front mounting section.
Fig. 14 is a schematic side view of fig. 13.
Fig. 15 is a schematic view of the D-D structure of fig. 14.
Fig. 16 is a schematic view of the E-E structure of fig. 14.
Fig. 17 is a schematic structural view of the cyclone core of the present invention.
Fig. 18 is a schematic cross-sectional structure of fig. 17.
Wherein, the figure compares: 1. the device comprises a duty nozzle, a main-stage spray rod, a front mounting section 3, a 4-vortex device, a 11-vortex core, a 12-nozzle pipe, a 13-duty nozzle cooling cover, a 14-duty nozzle rod, a 111-duty fuel inlet, a 112 circumferential hole, a 113-vortex chamber, a 114-nozzle, a 115-nozzle cooling hole, a 116-nozzle inlet, a 117-tangential spiral groove, a 211-stage spray rod fuel inlet, a 212-main-stage fuel spray rod nozzle, a front mounting section 31, a front mounting section cooling wall 32, a front mounting section air inlet 311, a 312-nozzle cooling hole, a 41-vortex device blade channel, a 42-vortex device throat and a 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 a valve shift nozzle 1, a main-stage spray rod 2, a front mounting section 3 and a swirler 4, wherein the components are assembled into a whole to jointly complete atomization and evaporation of fuel at the head 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 connected with the rear section of the front mounting section 3, the duty nozzle 1 is mounted on the central axis of the front mounting section 3, and the duty nozzle 1 is communicated to the swirler throat 42; a plurality of main-stage spray bars 2 are circumferentially arranged on the front end surface of the swirler 4 by taking the front mounting section 3 as a center, and spray holes of the main-stage spray bars 2 are communicated with 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 duty nozzle 1 is mainly used for fuel oil supply of a diffusion combustion flame stabilizing oil way; the main stage spray bar 2 is provided with a main stage fuel spray bar and a main stage gas spray bar, which are sequentially arranged along the air flow direction, and one air flow path can comprise a plurality of main stage fuel spray bars and main stage gas spray bars.
The main stage fuel spray boom is used for supplying liquid fuel for premixed combustion, and the main stage fuel spray boom is used for supplying gas fuel for premixed combustion, and the liquid fuel and the gas fuel form good initial atomization after being injected and form good evaporation blending with the airflow of the swirler 4.
The liquid fuel nozzle works as follows: the valve class fuel oil passes through the valve class nozzle 1 to form centrifugal conical oil mist to enter the throat 42 of the swirler, and diffusion combustion flame is formed near the central axis of the swirler 4 to stably burn; the main grade fuel is supplied through a main grade fuel spray rod, and spray generated by a main grade fuel spray rod nozzle 212 on the main grade fuel spray rod enters a vortex blade channel 41, is fully mixed with air flow in the vortex blade channel 41 and enters a vortex throat 42 for combustion after being evaporated; 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 to enter the swirler 4 to cool the front mounting section cooling wall 32, and meanwhile, part of the cooling air flows into the cooling cover inflow port 116 on the duty nozzle cooling cover 13 through the nozzle cooling holes 115 to be sprayed out to cool and thermally protect the duty nozzle 1.
Example 2
As shown in fig. 5-7, on the basis of embodiment 1, the duty nozzle 1 includes a cyclone core 11, a nozzle pipe 12, a duty nozzle cooling cover 13, and a duty nozzle rod 14, wherein the duty nozzle rod 14 is mounted on the top of the cyclone core 11, the tail end of the cyclone core 11 is sleeved with the nozzle pipe 12, and the outside of the nozzle pipe 12 is sleeved with the duty nozzle cooling cover 13; the top of the duty nozzle rod 14 is a duty fuel inlet 111, the central axial direction of the duty nozzle rod 14 is a duty fuel flow passage, the tail of the nozzle pipe 12 is funnel-shaped, and the bottom of the funnel is a nozzle 114.
The cyclone core 11 comprises a cylindrical section and a bottom end head at the top and the middle of the upper end, the top is conical or spherical, the top and the duty nozzle rod 14 form a conical or spherical sealing structure, the middle of the top and the cylindrical section is a communicated hollow structure, the bottom of the cylindrical section is an end face with a circumferential hole 112, and the bottom end face and the bottom end head of the cylindrical section are in solid connection; the top of the hollow structure is communicated with the duty grade fuel 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 with the central axis of the hollow structure as the center.
The bottom end head comprises a connecting rod and an end head, the diameter of the connecting rod is obviously smaller than that of the end head, and the connecting rod and the end head are similar to a screw structure with a screw cap; the connecting rod is connected with the cylindrical section, and the end head is clung to the inner wall surface of the tail part of the nozzle pipe 12; further, a tangential spiral groove 117 is formed in the outer wall surface of the end, a fuel oil swirl groove flow path is formed by the tangential spiral groove 117 and the inner wall surface of the spout pipe 12, and a swirl 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 main function of the cyclone core 11 is to form a ball cone seal with the duty nozzle rod 14, fuel is introduced from the duty fuel inlet 111, flows through the circumferential hole 112 and then passes through the tangential spiral groove 117, and is rotated into a cyclone chamber 113 formed by the front end wall surface of the cyclone core 11 and the inner wall surface of the nozzle. The fuel oil is subjected to rotary atomization and finally is sprayed out at the nozzle 114 in a rotational flow way to form an oil mist cone required by class diffusion flame.
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 port 116 is arranged on the side wall of the duty nozzle cooling cover 13 corresponding to the swirl chamber 113, and a nozzle cooling hole 115 is arranged on the bottom of the duty nozzle cooling cover 13 corresponding to the swirl chamber 113. The duty nozzle rod 14 is mainly used for sealing an oil path with the cyclone core 11, and simultaneously extending 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 fuel supply pipeline.
Example 3
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 channel, one end of the main-stage fuel flow channel is a main-stage spray rod fuel inlet 211, and the other end of the main-stage fuel flow channel is a main-stage spray rod fuel outlet; the side wall of the main-stage fuel spray rod is provided with a plurality of main-stage fuel spray rod nozzles 212 for flowing main-stage fuel, and the main-stage fuel spray rod nozzles 212 are communicated with a main-stage fuel flow passage in the middle of the main-stage spray rod 2.
The primary fuel flows in from the primary boom fuel inlet 211 on the primary boom, and the primary boom nozzle 212 adopts a simple orifice pressure atomization mode to obtain an initial atomized oil mist cone meeting the requirements, and the initial atomized oil mist cone is sprayed into the swirler vane passage 41.
10-12, the main fuel injection direction and the air flow direction are not perpendicular, but have a certain forward flow angle by adopting a structure with inclined holes on the main fuel injection rod nozzle 212, and the initial momentum of the fuel in the air flow inflow direction is utilized to ensure that fuel drops do not collide with walls in the swirler vane channel 41, thereby preventing long-time working coking and carbon deposition after fuel adhesion.
Example 4
As shown in fig. 13-16, on any of the embodiments 1-3, the outer wall surface of the front mounting section 3 is provided with a plurality of fan-shaped sections serving as the air inlets 311 of the front mounting section.
In this embodiment, three fan-shaped sections 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 cooling air throttling surface, and the conditions of loss or unsmooth flow and the like are avoided. Cooling air is injected into the swirler throat 42 through cooling holes 312 in the front mounting section stave 32, and the cooling holes 312 adopt an efficient mode with compound angular divergent cooling so that the cooling air can be effectively attached to the wall surface of the front mounting section stave 32, thereby not affecting the combustion process in the swirler 4.
Through the design, the working process of the invention is as follows:
the valve class fuel oil passes through the valve class nozzle 1 to form centrifugal conical oil mist to enter the throat 42 of the swirler, and diffusion combustion flame is formed near the central axis of the swirler 4 to stably burn; the main-stage fuel oil is supplied through the main-stage spray rod 2, and spray generated through spray holes of the main-stage spray rod 2 enters a swirler vane channel 41, is fully mixed with air flow in the swirler vane channel 41 and evaporated, and enters a swirler throat 42 for combustion;
combustion air enters through swirler air inlet 411 to participate in combustion; cooling air flows through cooling holes 312 on the front mounting section cooling wall 32 through the front mounting section air inlet 311 to enter the swirler 4 to cool the front mounting section cooling wall 32, and meanwhile, part of cooling air flows into the cooling cover inflow port 116 on the duty nozzle cooling cover 13 and is sprayed out through the nozzle cooling holes 115 to cool and thermally protect the duty nozzle 1;
in the class nozzle 1, fuel is introduced and supplied from an on-duty fuel inlet 111, flows through the top of the cyclone core 11 and the cylindrical section, flows out of a circumferential hole 112 at the bottom of the cylindrical section, and flows through a fuel cyclone groove flow path formed by a tangential spiral groove 117 to rotate the fuel into a cyclone chamber 113; after rotary atomization, the fuel is finally sprayed out by rotational flow at a nozzle to form an oil mist cone required by class diffusion flame; at this time, the on-duty nozzle 1 is cooled and protected by a cooling air channel between the on-duty nozzle cooling cover 13 and the outer wall surface of the nozzle pipe 12, and after the cooling air enters from the front mounting section air inlet 311, a very small part of the cooling air flows into the on-duty nozzle 1 through the cooling cover inflow opening 116 on the on-duty nozzle cooling cover 13 and is sprayed out from the nozzle cooling hole 115, so that a layer of cooling air film protection on-duty nozzle 1 is formed; the duty nozzle rod 14 and the cyclone core 11 are in oil way sealing, and meanwhile, the fuel supply pipeline is prolonged, so that the oil way extends out of the swirler 4 and the front mounting section 3 so as to be connected with an external fuel supply pipeline;
the primary fuel flows in from the primary boom fuel inlet 211 on the primary boom, and the primary boom nozzle 212 adopts a pore pressure atomization mode to obtain an initial atomized oil mist cone meeting the requirements, and the initial atomized oil mist cone is sprayed into the swirler vane channel 41.
The liquid fuel nozzle of the present invention has the following two modes of operation:
(1) Small load state operation mode
In the ignition and small load state, only the valve-class nozzle 1 works, fuel oil only forms centrifugal conical oil mist through the valve-class nozzle 1 to enter the swirler throat 42, and diffusion combustion flame is formed near the central axis of the swirler 4.
The principle of the small load state working mode is as follows: in view of the fact that the fuel supply amount and the air inflow are smaller at this time, the emission standard does not prescribe or require the emission in a small state, so that the stable process of combustion is mainly considered, a pure diffusion combustion mode is adopted, the advantages of good diffusion combustion stability and difficulty in generating combustion oscillation and pressure pulsation are utilized, and good combustion stability is obtained under the working conditions of a small state with lower pressure and temperature. Meanwhile, because the small-state oil gas is relatively low, after all the fuel oil is concentrated on the duty level for supply, the fuel oil can be combusted in a main combustion area by obtaining more proper oil gas ratio, and the combustion efficiency of the small state can be greatly improved and ensured.
(2) Large load state operation mode:
in a state of higher load, a small amount of fuel forms centrifugal conical oil mist from the duty nozzle 1 to enter the throat 42 of the swirler, and forms diffusion combustion flame near the central axis of the swirler 4; a large amount of fuel is sprayed from the primary fuel boom nozzle 212 on the primary fuel boom into the swirler vane passage 41, fully mixed with the air flow in the swirler vane passage 41 for evaporation, 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 ensured by the class diffusion flame, a large amount of fuel enters the swirler vane passage 41 through the main-stage spray rod 2, the fuel is ensured not to collide with the wall by adopting an inclined spraying mode, and the uniformity of the premixed flame is ensured by uniformly mixing and evaporating the fuel with high-temperature air in the swirler vane passage 41; the combustion areas can be ensured to burn under a proper equivalent ratio by means of the class and main grade fuel oil partition modes, and the generation of NOx is effectively controlled, so that good pollution emission is realized.
Claims (4)
1. A liquid fuel nozzle for a dual-radial swirler dual-fuel combustion chamber, characterized by: the intelligent air-conditioning system comprises a class-on-duty nozzle (1), a main-stage spray rod (2), a front mounting section (3) and a vortex device (4), wherein the front end of the vortex device (4) is fixedly connected with the front mounting section (3), the class-on-duty nozzle (1) is mounted on the central axis of the front mounting section (3), and the class-on-duty nozzle (1) is communicated to a vortex device throat (42); a plurality of main-stage spray bars (2) are circumferentially arranged on the front end surface of the swirler (4) by taking the front mounting section (3) as the center, and spray holes of the main-stage spray bars (2) are communicated with a swirler blade 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 duty nozzle (1) is used for supplying fuel to a diffusion combustion flame stabilizing oil way; the main-stage fuel spray rod (2) is provided with a main-stage fuel spray rod and a main-stage fuel spray rod, 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 formed into evaporation blending with the airflow of the swirler (4) after being sprayed;
the on-duty nozzle (1) comprises a cyclone 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 cyclone core (11), the nozzle pipe (12) is sleeved at the tail end of the cyclone core (11), and the on-duty nozzle cooling cover (13) is sleeved outside the nozzle pipe (12); the top of the duty nozzle rod (14) is a duty fuel inlet (111), the central axial direction of the duty nozzle rod (14) is a duty fuel flow passage, the tail of the nozzle pipe (12) is funnel-shaped, and the bottom of the funnel is a nozzle (114); the cyclone core (11) comprises an upper end top, a middle cylindrical section and a bottom end head, wherein the top is conical or spherical, the top and the duty-level nozzle rod (14) form a conical or spherical sealing structure, the middle of the top and the cylindrical section is of a communicated hollow structure, the bottom of the cylindrical section is an end face with a circumferential hole (112), and the bottom end face 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 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 with the central axis of the hollow structure as the center; the bottom end head comprises a connecting rod and an end head, a tangential spiral groove (117) is formed in the outer wall surface of the end head, a fuel oil rotational flow groove flow path is formed by the tangential spiral groove (117) and the inner wall surface of the spout pipe (12), and a rotational flow chamber (113) is formed in 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);
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 inflow port (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 axial middle of the main-stage fuel spray rod is provided with a main-stage fuel flow channel, one end of the main-stage fuel flow channel is provided with a main-stage spray rod fuel inlet (211), and the other end of the main-stage fuel flow channel is provided with a main-stage spray rod fuel outlet; the side wall of the main-stage fuel spray rod is provided with a plurality of main-stage fuel spray rod nozzles (212) for flowing in main-stage fuel, and the main-stage fuel spray rod nozzles (212) are communicated with a main-stage fuel runner in the middle of the main-stage fuel spray rod; the main-stage fuel spray rod nozzle (212) is of an inclined hole structure, so that a certain forward flow angle exists between the liquid fuel injection direction and the air flow direction;
the outer wall surface of the front mounting section (3) is provided with a plurality of fan-shaped sections serving as front mounting section air inlets (311), cooling air is introduced through the front mounting section air inlets (311), and the area of the front mounting section air inlets (311) is larger than that of the 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 surface of the front mounting section stave (32).
2. A liquid fuel nozzle for a dual radial swirler dual fuel combustion chamber as claimed in claim 1, wherein: the diameter of the connecting rod of the bottom end is smaller than that of the end; the connecting rod is connected with the cylindrical section, and the end head is clung to the inner wall surface of the tail part of the nozzle pipe (12).
3. 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 valve class fuel oil passes through the valve class nozzle (1) to form centrifugal conical oil mist to enter the throat (42) of the swirler, and diffusion combustion flame is formed near the central axis of the swirler (4) to stabilize combustion; the main grade fuel is supplied through a main grade fuel spray rod, spray generated through spray holes of the main grade fuel spray rod enters a swirler vane channel (41), and enters a swirler throat (42) for combustion after being fully mixed and evaporated with air flow in the swirler vane channel (41);
combustion air enters through a swirler air inlet (411) to participate in combustion; cooling air flows through cooling holes (312) in the cooling wall (32) of the front mounting section through an air inlet (311) of the front mounting section, enters the 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 port (116) in the duty nozzle cooling cover (13) and is sprayed out through a nozzle cooling hole (115) to cool and thermally protect the duty nozzle (1);
in the class nozzle (1), fuel is introduced from a class fuel inlet (111), flows through the top of a swirl core (11) and a cylindrical section, flows out of a circumferential hole (112) at the bottom of the cylindrical section, and flows through a fuel swirl groove flow path formed by tangential spiral grooves (117) to enable the fuel to rotate into a swirl chamber (113); after rotary atomization, the fuel is finally sprayed out by rotational flow at a nozzle to form an oil mist cone required by class diffusion flame; the cooling air channel between the duty nozzle cooling cover (13) and the outer wall surface of the nozzle pipe (12) is used for cooling and protecting the nozzle, and after the cooling air enters from the air inlet (311) of the front mounting section, a very small part of cooling air flows into the nozzle through the cooling cover inflow opening (116) on the duty nozzle cooling cover (13) and is sprayed out from the nozzle cooling hole (115) to form a layer of cooling air film protecting nozzle; the class nozzle rod (14) and the cyclone core (11) are in oil way sealing, and meanwhile, the 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 fuel supply pipeline;
the primary fuel flows in from a primary spray rod fuel inlet (211) on the primary fuel spray rod, and an initial atomized oil mist cone meeting the requirement is obtained by adopting a hole pressure atomization mode through a primary fuel spray rod nozzle (212) and is sprayed into a vortex blade channel (41).
4. 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) Small load state operation mode: under the ignition and small load state, only the duty nozzle (1) works, fuel oil only forms centrifugal conical oil mist through the duty nozzle (1) to enter the throat (42) of the swirler, and diffusion combustion flame is formed near the central axis of the swirler (4);
(2) Large load state operation mode: in a state of higher load, a small amount of fuel forms centrifugal conical oil mist from the duty nozzle (1) to enter a throat (42) of the swirler, and forms diffusion combustion flame near the central axis of the swirler (4); a large amount of fuel is sprayed from spray holes on a main-stage fuel spray rod to enter a swirler vane channel (41), and enters a swirler throat (42) for premixed combustion after being fully mixed and evaporated with air flow in the swirler vane channel (41).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Application Number | Priority Date | Filing Date | Title |
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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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| CN114034061A CN114034061A (en) | 2022-02-11 |
| CN114034061B true CN114034061B (en) | 2023-06-23 |
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| CN114738799B (en) * | 2022-04-20 | 2024-03-26 | 新奥能源动力科技（上海）有限公司 | Head assembly of dual-fuel combustion chamber, combustion chamber and gas turbine |
| CN114838386B (en) * | 2022-04-20 | 2023-06-23 | 中国航发沈阳发动机研究所 | Gas fuel nozzle for low-pollution combustion chamber |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN201225656Y (en) * | 2008-05-12 | 2009-04-22 | 哈尔滨东安发动机（集团）有限公司 | Air atomizing nozzle |
| CN107575891B (en) * | 2017-07-25 | 2019-08-09 | 西北工业大学 | A kind of dual-fuel gas turbine low pollution combustor head construction |
| CN107796016A (en) * | 2017-09-29 | 2018-03-13 | 哈尔滨理工大学 | A kind of gas-turbine combustion chamber double fuel integrated spray nozzle device |
| CN110107916B (en) * | 2019-05-15 | 2020-11-13 | 哈尔滨电气股份有限公司 | Dry-type low-pollution combustion chamber double-radial swirl nozzle for gas turbine |
| CN110440292B (en) * | 2019-07-26 | 2020-12-01 | 中国航发沈阳发动机研究所 | Combustor of combustion chamber of gas turbine |
| CN113251440B (en) * | 2021-06-01 | 2021-11-30 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
| CN113251439B (en) * | 2021-06-24 | 2021-11-16 | 成都中科翼能科技有限公司 | Double-stage co-rotating head device for dual-fuel gas turbine |
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