CN204961141U - Air atomizing fuel spray nozzle device - Google Patents

Abstract

The utility model relates to an air atomization fuel nozzle device, which is applied to a high-temperature rising combustion chamber. The head swirler includes a central duty unit and a peripheral main combustion unit, and the central duty unit adopts a two-stage axial swirler structure , the oil film formed by the fuel on duty is atomized under the shearing action of the two-stage axial swirling air inside and outside the duty class, forming an oil-rich diffusion combustion mode in the duty class to avoid the high-temperature rise combustion chamber caused by the large gas volume at the head Combustion instability problem under low power; the main combustion stage adopts a two-stage counter-rotating combined swirler structure with a weak swirl design, the inner stage is an axial swirler, the outer stage is a radial swirler, and the main The combustion-grade fuel is sprayed downstream of the radial swirler vane channel of the outer stage of the main combustion stage through multiple fuel injection holes, and after the atomization and mixing of the two-stage swirling air inside and outside the main combustion stage, the oil-air mixture in the premixing channel of the main combustion stage The distribution is uniform, forming a premixed combustion mode, and avoiding the problem of exhaust smoke at the outlet of the combustion chamber under high power of the high-temperature rise combustion chamber. The utility model is mainly used in a high-temperature combustion chamber of an aero-engine with an increased oil-gas ratio, and can also be used in a low-pollution combustion chamber of a civil aero-engine and an industrial gas turbine, so as to improve the mixing of oil and gas in the combustion chamber and reduce the discharge of pollutants at the outlet of the combustion chamber.

Description

An air atomizing fuel nozzle device

technical field

The utility model is suitable for a combustion chamber of an aero-engine with high-temperature-raised oil-gas ratio, and relates to an air atomization fuel nozzle device.

Background technique

The thrust-to-weight ratio of military aeroengines is getting higher and higher, which requires continuous improvement of the temperature rise of the combustion chamber. The high temperature rise corresponds to a high oil-gas ratio. In a high-oil-gas ratio environment, if the conventional swirl cup type oil-gas mixing scheme is adopted, the amount of air actually participating in the head combustion is small due to the intake air from the main combustion hole and the mixing hole. The head equivalence ratio will be far more than 1, and there will be serious smoke in the combustion chamber under high power. However, invisible smoke from the exhaust of aero-engines is a requirement for environmental protection, and it is also a tactical requirement for military engines. Because the exhaust smoke means a lot of hot fine carbon particles, these hot carbon particles will trigger the far infrared, and many air-to-air missiles are equipped with far infrared guidance devices. Therefore, in order to solve the problem of visible smoke in the high-temperature rise combustion chamber, it is necessary to greatly increase the air intake at the head, remove the intake air from the main combustion hole, and reduce or even eliminate the intake air from the mixing hole. When there is a large amount of gas in the head, if the single-channel fuel supply scheme of the conventional combustion chamber is still used, there will be a problem of unstable combustion at low power. The solution to this problem is to adopt a fuel supply scheme similar to the low-pollution combustion chamber TAPS (TwinAnnualPremixingSwirler). That is to say, at low power, only the fuel supply of the center duty stage is required to ensure the combustion stability, and at high power, the duty stage and the main combustion stage are simultaneously supplied with fuel to meet the requirement of no visible smoke from the exhaust of the high-temperature rise combustion chamber.

Referring to the TAPS solution, Beijing University of Aeronautics and Astronautics applied for several patents on low-pollution combustors with integrated fuel injection, the application numbers are 200810104684.4, 200810104686.3 and 200810105061.9. Differences in spray patterns. For example, in the patents with application numbers 200810104684.4 and 200810105061.9, the main combustion stage adopts a one-stage radial swirler structure, and the fuel is injected axially into the premixing channel of the main combustion stage. position of the spray nozzle. The patented main combustion stage with application number 200810104686.3 is a first-stage axial swirler, and the fuel injection point of the main combustion stage is located in the inner ring of the main combustion stage, in the middle of the blades of the main combustion stage or in the outer ring of the main combustion stage. These patents propose a combustor head structure and an oil-gas mixing scheme that can meet the design requirements of a low-pollution combustor with a relatively low air intake in the head and a relatively low oil-air ratio. In the high-temperature rise combustor, the number of swirlers in the main combustion stage is small, and the swirl structure is relatively simple, so it is difficult to achieve efficient and rapid oil-gas mixing at the head of the combustor.

In some patents applied by GE, the strong swirl flow design of the main combustion stage and the weak swirl flow design of the duty stage are adopted, so that the return flow in the combustion chamber is dominated by the main combustion stage. The air of the peripheral main combustion stage with more gas volume has a weaker effect on the fuel-rich central duty stage, which makes the duty stage oil and gas mix unevenly, which is not conducive to the improvement of the temperature distribution of the combustion chamber outlet.

Utility model content

The technical problem to be solved by the utility model is: to overcome the deficiencies of the above-mentioned prior art, adopt a multi-stage combined cyclone structure to strengthen the mixing of fuel and air in the head, and avoid visible smoke at the outlet of the combustion chamber; The design idea of the weak swirl flow in the main combustion stage of the main flow is that the swirl flow on duty is used to dominate the return flow of the combustion chamber, and the oil-gas mixing at the duty level is strengthened, thereby improving the temperature distribution at the exit of the combustion chamber.

The technical solution adopted by the utility model to solve the technical problem is: an air atomized fuel nozzle device, the head swirler includes a central duty class unit and a peripheral main combustion unit, and is characterized in that:

--The central duty level unit includes a central diversion cone arranged coaxially from the inside to the outside, the duty level inner axial swirler, the duty level oil film nozzle and the duty level outer axial swirler, wherein ,

The on-duty oil film nozzle is an annular sleeve structure with a sandwich, including an inlet section, a transition section and an outlet section connected in sequence; the space between the inner wall surface of the on-duty oil film nozzle and the central diversion cone constitutes the second an airflow channel;

The interlayer in the duty-level oil film nozzle constitutes the duty-level oil supply channel, and the interlayer includes a duty-level oil cavity basically located on the inlet section of the duty-level oil film nozzle and a transition section and an outlet section of the duty-level oil film nozzle. One end of the duty-grade oil circuit communicates with the duty-grade oil cavity, and the other end communicates with the slit arranged on the inner wall surface of the outlet section of the duty-grade oil film nozzle, and the slit constitutes the duty-grade oil film nozzle ;

--The peripheral main combustion stage unit includes a transitional annular sleeve, an annular main combustion stage oil supply plate, a peripheral annular sleeve, the main combustion stage inner stage axial swirler and the main combustion stage outer stage radial swirler, in,

The transitional annular sleeve is sleeved on the outlet section of the duty-level oil film nozzle, and the duty-level outer axial swirler is arranged between the two, and the inner wall of the transitional annular sleeve constitutes the second air flow channel , the space between the inner wall surface of the inlet section of the transition annular sleeve and the outer wall surface of the outlet section of the duty-grade oil film nozzle constitutes the inlet section of the second airflow channel, and the outlet section of the airflow channel has a certain clamping distance with the central axis Angle; the inner wall part of the transition annular sleeve beyond the duty grade oil film nozzle constitutes the expansion section of the second airflow channel;

The annular main fuel stage oil supply plate includes a main fuel stage layered partition arranged at its inner circumference, a main fuel stage oil chamber located on its back side, and a main fuel stage oil chamber located on its outer surface and communicating with the main fuel stage oil chamber The fuel injection hole of the main combustion stage; the axial swirler of the internal stage of the main combustion stage is arranged in the third airflow channel between the inlet section of the transition annular sleeve and the layered partition of the main combustion stage; the The outer stage radial swirler of the main combustion stage is arranged in the fourth airflow passage between the annular main combustion stage oil supply plate and the peripheral annular sleeve;

The internal stage axial swirler of the main combustion stage and the radial swirler of the external stage of the main combustion stage are separated by the layered partition of the main combustion stage; the inner wall surface of the peripheral annular sleeve constitutes the main combustion stage stage premix channel.

In the air atomizing fuel nozzle device of the present utility model, the central duty class unit adopts a two-stage swirler structure, including the duty class inner axial swirler and the duty class outer shaft coaxially arranged with the central diversion cone. The duty-grade fuel enters the duty-grade oil cavity, and forms an oil film evenly distributed in the circumferential direction after flowing through the duty-grade oil circuit. The swirling shear effect forms duty-grade oil mist in the duty-grade expansion channel. The peripheral main combustion stage unit adopts a two-stage combined swirler structure, including the main combustion stage inner stage axial swirler and the main combustion stage outer stage radial swirler. layer dividers. The main fuel oil enters the main fuel chamber, and the fuel in the main fuel chamber is directly injected downstream of the main fuel stage radial swirler vane channel through the main fuel injection hole, forming multiple main fuel oil streams The jet flow is successively subjected to the atomization and mixing of the two reverse-rotating swirling air inside and outside the main combustion stage, forming a uniformly distributed oil-gas mixture in the premixing channel of the main combustion stage, and finally entering the combustion zone for combustion to improve high-temperature rise combustion The purpose of indoor oil and gas mixing.

Preferably, the airflow rotation direction of the duty-level inner-stage axial swirler is the same as or opposite to the airflow rotation direction of the duty-stage outer-stage axial swirler.

Preferably, the rotation direction of the airflow of the axial swirler in the main combustion stage is the same as or opposite to that of the axial swirler in the outer stage of the duty stage, and the rotation direction of the radial swirler in the outer stage of the main combustion stage is The direction is perpendicular to the airflow rotation direction of the axial swirler in the main combustion stage.

Preferably, the main combustion stage fuel injection hole is located downstream of the main combustion stage outer radial swirler vane channel, and the number of main combustion stage outer radial swirler vane passages is an integer multiple of the main combustion stage fuel injection hole number , The main fuel injection holes are evenly distributed along the circumference.

Preferably, the diameter of the fuel injection hole of the main combustion stage ranges from 0.4 mm to 1.2 mm.

Preferably, the ratio of the radial height of the main combustion stage fuel injection hole to the radial height of the main combustion stage stratified partition is in the range of 1.1-1.3.

Preferably, the ratio of the length of the layered partitions of the main combustion stage to the fuel injection hole of the main combustion stage to the outlet of the swirler of the main combustion stage is in the range of 0-0.5.

Preferably, the air volume of the central duty class unit accounts for 10%-20% of the total intake air volume of the combustion chamber, the air volume of the peripheral main combustion stage units accounts for 65%-75% of the total air intake volume of the combustion chamber, and the duty class internal stage The gas volume of the axial swirler accounts for 30%-70% of the gas volume of the central duty unit, and the gas volume of the axial swirler in the main combustion stage accounts for 20%-80% of the gas volume of the peripheral main combustion unit.

Preferably, all the gas required for combustion enters from the head swirler, and there are no main combustion holes and mixing holes on the flame tube, only cooling holes.

The working principle of the utility model: the central duty class unit adopts the pre-film air atomization method, and the oil film is broken under the action of swirling air at two levels of different speeds inside and outside the duty class, forming oil-rich diffusion combustion. The fuel jet formed by the multi-point injection of the main combustion fuel is rapidly mixed with the air under the action of the radial swirl of the outer stage of the main combustion stage, and then is subjected to the action of the axial reverse swirling air of the inner stage of the main combustion stage, so that the fuel The mixing is more uniform in the main combustion stage premixing channel, and the main combustion stage premixing combustion is realized. This combustion method can take into account the combustion stability of the high-temperature combustion chamber at low power and the invisible smoke of the exhaust gas at high power. There are no main combustion holes and mixing holes on the flame tube of the combustion chamber, but only cooling holes. The purpose is to increase the air intake at the head, reduce the equivalence ratio of the head, and further control the exhaust smoke at the outlet of the combustion chamber.

The central duty unit is started under low power conditions such as idling, and adopts a fuel-rich diffusion combustion method to avoid the problem of combustion instability caused by the increase in the head intake air volume of the high-temperature rise combustion chamber. When the engine power increases, start the peripheral main combustion unit. Since the peripheral main combustion unit adopts the premixed combustion method, the total equivalent ratio of the main combustion area of the combustion chamber is lower than 1.2, so as to avoid the high temperature rise of the combustion chamber due to the high ratio of oil and gas. Possible exhaust visible smoke problems.

Although from the perspective of combustion organization, the use of diffusion combustion in the on-duty stage and premixed combustion in the main combustion stage can solve the contradiction between low-power and high-power working conditions in the high-temperature rise combustion chamber, the uniformity of oil-gas mixing in the main combustion stage is the main factor that affects the high temperature. The direct factor of whether there is visible smoke in the liter combustion chamber under large working conditions. The main combustion stage adopts a two-stage combined swirler structure, which can effectively avoid local fuel-rich areas in the combustion chamber caused by a single swirl structure, and make the fuel and air mix more uniformly.

Due to the large air intake at the head of the high-temperature rise combustion chamber, the main combustion hole and the mixing hole are not set on the flame tube, and the design idea of strong swirl flow in the main combustion stage and weak swirl in the duty class is adopted, and the return flow in the combustion chamber is dominated by the duty class , which is conducive to entraining the inner layer air of the main combustion stage into the recirculation area of the duty stage, strengthening the oil-gas mixing of the duty stage, reducing the peak temperature of the duty stage, thereby improving the outlet temperature distribution of the combustion chamber without mixing holes.

The utility model has the following advantages compared with the prior art:

1. The main fuel stage of the utility model adopts a two-stage combined swirler structure, and the fuel oil of the main fuel stage is sprayed downstream of the blade channel of the radial swirler on the outer stage of the main fuel stage, and is mixed with the radial swirl air for the first time. After the layered partition between the two-stage cyclone of the main combustion stage, the oil-air mixture is mixed with the axial swirl air in the main combustion stage, which strengthens the mixing of fuel and air in the premixing channel of the main combustion stage, effectively avoiding Emergence of localized oil-rich regions.

2. The gas volume distribution between the inner and outer two-stage cyclone of the main combustion stage of the utility model is adjusted to the optimal ratio according to the actual oil-gas mixing effect. The diameter, number and radial position of the fuel injection holes of the main combustion stage can also be adjusted according to the actual oil-air mixing effect.

3. The two-stage axial cyclone of the duty class of the utility model has the same or opposite rotation direction of the airflow, and the air volume distribution between the two-stage cyclone inside and outside the duty class is adjusted to make the duty class form a strong swirl; the internal stage of the main combustion stage The rotation direction of the airflow of the axial swirler and the radial swirler of the outer stage is opposite, so that the main combustion stage forms a weak swirl, and realizes that the duty stage dominates the return flow in the combustion chamber.

4. All the air required for combustion in the combustion chamber of the utility model enters from the head, and the main combustion hole and the mixing hole are not opened on the flame tube, so as to reduce the average equivalent ratio of the main combustion area and avoid smoking under heavy working conditions.

5. The layered combustion method of the duty-level diffusion combustion and the main combustion-level premixed combustion of the utility model takes into account the stable operation of the high-temperature rising combustion chamber at low power and the invisible exhaust smoke at high power.

Description of drawings

Fig. 1 is a schematic diagram of the structure of a high temperature rising combustion chamber;

Figure 2 is an enlarged schematic view of the head cyclone;

Figure 3 is a schematic diagram of the radial position of the main fuel injection hole.

detailed description

In order to make the purpose, technical solutions and advantages of the utility model clearer, the utility model will be further described in detail below with reference to the accompanying drawings and examples.

Fig. 1 is a schematic diagram of a combustion chamber 10 with a high-temperature raising oil-gas ratio, which is a straight-line single-annular cavity structure, and 10 includes a diffuser 11, an outer casing 12, an inner casing 13, a cap 14, and a head end Wall 15, outer flame tube 16, inner flame tube 17 and head swirler 18. The high-pressure air is decelerated and diffused by the diffuser 11 and divided into three routes. The first route of air passes through the head swirler 18 and mixes with the fuel, and then enters the combustion zone 19 to participate in combustion. The second and third routes of air flow through the outer casing 12 respectively. The two annular cavities between the outer flame tube 16 and the inner casing 13 and the inner flame tube 17 enter the cooling holes (not shown in the figure) provided on the outer flame tube 16 and the inner flame tube 17 for cooling the wall surface of the flame tube , to ensure the life of the combustion chamber. There are no main combustion holes and mixing holes on the wall of the inner and outer flame tubes, only cooling holes. The first air volume accounts for 75% to 85% of the intake air volume of the combustion chamber, the purpose of which is to reduce the average equivalence ratio of the combustion zone 19 and avoid smoking under heavy working conditions. FIG. 2 is an enlarged view of the head swirler 18 in FIG. 1 , which structurally includes a central shift unit 20 and a peripheral main combustion unit 21 . The air volume of the central duty class unit 20 accounts for 10%-20% of the intake air volume of the combustion chamber, and the air volume of the peripheral main combustion level unit 21 accounts for 65%-75% of the air intake volume of the combustion chamber.

The central duty level unit 20 includes a central diversion cone 201 coaxially arranged from the inside to the outside, a duty level inner axial swirler 22, a duty level oil film nozzle 202 and a duty level outer axial swirler 23, Referring to Fig. 2, the central diversion cone 201 includes a cylindrical section on the airflow inlet side and a conical section near the airflow outlet side, and the duty-level inner stage axial swirler 22 is sleeved on the cylindrical section of the central diversion cone 201 The oil film nozzle 202 on duty is an annular sleeve structure with interlayer, including an inlet section, a transition section and an outlet section connected in sequence, wherein the size of the inlet section is greater than the size of the outlet section; the inner wall surface and the center of the oil film nozzle 202 on duty The space between the diversion cones 201 constitutes the first air flow channel, the diameter of the inlet section of the air flow channel is greater than the diameter of the outlet section; The duty level oil cavity 25 on the oil film nozzle inlet section and the duty level oil circuit 26 located on the duty level oil film nozzle transition section and the exit section, one end of the duty level oil circuit 26 communicates with the duty level oil cavity 25, and the other end is connected to the The slit on the inner wall surface of the outlet section of the on-duty oil film nozzle 202 is connected, and the slit constitutes the on-duty oil film nozzle. The duty level outer axial swirler 23 is sleeved on the outlet section of the duty level oil film nozzle 202 .

The peripheral main combustion stage unit 21 includes a transitional annular sleeve 211, an annular main combustion stage oil supply plate 212, a peripheral annular sleeve 213, the main combustion stage inner stage axial swirler 20 and the main combustion stage outer stage radial swirler 31. The transitional annular sleeve 211 is sleeved on the outlet section of the duty-level oil film nozzle 202, and the duty-level outer-stage axial swirler 23 is arranged between the two. The inner wall of the transitional annular sleeve 211 constitutes the second air flow channel, and the transition The space between the inner wall surface of the inlet section of the annular sleeve 211 and the outer wall surface of the duty-grade oil film nozzle 202 outlet section constitutes the inlet section of the second airflow channel, and the outlet section of the airflow channel has a certain angle with the central axis; the transition ring The part of the inner wall surface of the sleeve 211 beyond the on-duty oil film nozzle 202 constitutes the expansion section of the second airflow channel.

The annular main fuel stage oil supply plate 212 includes a main fuel stage layered separator 30 arranged at its inner circumference, a main fuel stage oil cavity 33 located on its back side and a The fuel injection hole 34 of the main combustion stage; the axial swirler 29 of the internal stage of the main combustion stage is arranged in the third airflow channel between the inlet section of the transition annular sleeve 211 and the layered partition plate 30 of the main combustion stage; The stage radial swirler 31 is arranged in the fourth air flow passage between the annular main fuel stage oil supply plate 212 and the peripheral annular sleeve 213 . The inner stage axial swirler 29 of the main combustion stage and the radial swirler 31 of the outer stage of the main combustion stage are separated by a layered partition 30 of the main combustion stage; Mix channel 36.

Duty grade fuel oil 24 enters the duty grade oil chamber 25, flows through the longer duty grade oil passage 26, and forms an oil film along the circumferential direction. 23 breaks under the action of swirl shear, and forms duty-grade oil mist with a certain cone angle in the duty-grade expansion channel 28. With the strong swirling effect of the duty class, the oil mist spreads to the combustion zone 19 for combustion.

The peripheral main combustion stage 21 includes the main combustion stage inner stage axial swirler 29 , the main combustion stage layered separator 30 , and the main combustion stage outer stage radial swirler 31 . The main fuel oil 32 enters the main fuel cavity 34, and the fuel is ejected from multiple main fuel injection holes 34, forming multiple main fuel jets 35 downstream of the main fuel radial swirler vane channel 40 , under the action of the swirling air of the outer stage radial swirler 31 of the main combustion stage, the fuel and air are mixed for the first time. The swirling air participates in the mixing of oil and gas in the main combustion stage 21, so that the fuel oil in the premixing channel 36 of the main combustion stage is distributed more evenly, effectively avoiding exhaust smoke caused by local rich oil.

For combustion chambers with neither main combustion holes nor mixing holes, the duty-level strong swirl main combustion-level weak swirl design is adopted, the purpose of which is to form the backflow in the combustion chamber by the duty-level swirl, which is beneficial to the main Part of the air in the combustion stage is entrained to the central oil-rich combustion area, which strengthens the oil-gas mixing in this area and reduces the peak temperature of the duty stage, thereby improving the temperature distribution at the outlet of the combustion chamber. Therefore, the rotation direction of the air flow of the duty class inner stage axial swirler 22 and the duty class outer stage axial swirler 23 can be the same or opposite, by adjusting the air volume distribution between the duty class 20 inner and outer two stage swirlers, so that The duty level 20 reaches a strong swirl flow; the airflow rotation direction of the main combustion stage inner stage axial swirler 29 and the main combustion stage outer stage radial swirler 31 is opposite, the purpose is to weaken the main combustion stage 21 swirl intensity, and at the same time Strengthen the oil-gas mixing in the premixing channel 36 of the main combustion stage; the direction of rotation of the airflow between the outer stage axial swirler 23 of the duty stage and the inner stage axial swirler 29 of the main combustion stage can be the same or opposite, which is determined by the actual combustion The working performance of the chamber is determined, such as the ignition limit of the combustion chamber and other parameters.

Considering the atomization effect of the main combustion stage fuel jet 35 in the lateral air flow of the main combustion stage outer radial swirler 31, it is necessary to reasonably select the main combustion stage fuel injection hole diameter 41 and the number of main combustion stage fuel injection holes 34. Generally, the main combustion stage The fuel injection hole diameter 41 of the combustion stage is between 0.4mm and 1.2mm, and the number of the radial swirler vane passages 40 of the outer stage of the main combustion stage is an integral multiple of the number of the fuel injection holes 34 of the main combustion stage. In order to make the oil-gas mixture in the premixing channel 36 of the main combustion stage more uniform, the position of the fuel injection hole 34 of the main combustion stage needs to be arranged reasonably. Figure 3 shows the radial position of the fuel injection hole of the main combustion stage. The ratio of the height 42 to the radial height of the main combustion stage layered partition is in the range of 1.1-1.3, so that the fuel oil at the outlet 37 of the main combustion stage swirler is reasonably distributed in the radial direction.

Adjusting the length 38 of the main combustion stage layered separator 30 in Fig. 1 can control the primary atomization mixing length of the main combustion stage outer stage radial swirler 31 to the main combustion stage fuel jet 35 and the main combustion stage internal stage axial swirl. The remixing length of the flow device 29 to the main combustion stage fuel jet 35, the shorter the main combustion stage layered partition 30, the shorter the initial mixing length of the main combustion stage outer radial swirler 31 and the main combustion stage internal stage The longer the remixing length of the axial swirler 29 is, the ratio of the length 38 of the main combustion stage stratified partition to the distance 39 from the main combustion stage fuel injection hole to the outlet of the main combustion stage swirler is selected within the range of 0 to 0.5, To obtain the best homogeneity of the main fuel grade oil-air mixture.

When the engine starts or works in a low-power state, the central duty class unit 20 supplies oil, and the peripheral main combustion unit 21 only enters air without supplying oil, and the duty class oil mist 27 forms a diffusion combustion mode in the combustion zone 19, thereby ensuring It improves the combustion stability of the high-temperature rise combustion chamber due to the large intake air volume at the head. When the engine works in a high-power state such as climbing or cruising, the duty stage 20 and the main fuel stage 21 supply oil at the same time, and the multiple fuel jets 35 injected by the main fuel stage fuel oil 32 through the main fuel stage fuel injection hole 34 are received by the main fuel stage 21. The horizontal jet atomization of the inner and outer two-stage swirling air forms premixed oil and gas in the premixing channel 36 of the main combustion stage, and enters the combustion zone 19 to form a premixed combustion mode, so that the equivalent ratio of the main combustion zone is lower than 1.2, thereby ensuring The high-temperature rise of the combustion chamber is not visible at the outlet of the high-power exhaust smoke.

The above descriptions are only preferred embodiments of the present utility model, and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. within the spirit and principles of the present utility model shall include Within the scope of the present utility model.

Claims (9)

1. An air atomizing fuel nozzle device, comprising a central duty unit and a peripheral main combustion unit, characterized in that: --The central duty level unit includes a central diversion cone arranged coaxially from the inside to the outside, the duty level inner axial swirler, the duty level oil film nozzle and the duty level outer axial swirler, wherein , The on-duty oil film nozzle is an annular sleeve structure with a sandwich, including an inlet section, a transition section and an outlet section connected in sequence; the space between the inner wall surface of the on-duty oil film nozzle and the central diversion cone constitutes the second an airflow channel; The interlayer in the duty-level oil film nozzle constitutes the duty-level oil supply channel, and the interlayer includes a duty-level oil cavity basically located on the inlet section of the duty-level oil film nozzle and a transition section and an outlet section of the duty-level oil film nozzle. One end of the duty-grade oil circuit communicates with the duty-grade oil cavity, and the other end communicates with the slit arranged on the inner wall surface of the outlet section of the duty-grade oil film nozzle, and the slit constitutes the duty-grade oil film nozzle ; --The peripheral main combustion stage unit includes a transitional annular sleeve, an annular main combustion stage oil supply plate, a peripheral annular sleeve, the main combustion stage inner stage axial swirler and the main combustion stage outer stage radial swirler, in, The transitional annular sleeve is sleeved on the outlet section of the duty-level oil film nozzle, and the duty-level outer axial swirler is arranged between the two, and the inner wall of the transitional annular sleeve constitutes the second air flow channel , the space between the inner wall surface of the inlet section of the transition annular sleeve and the outer wall surface of the outlet section of the duty-grade oil film nozzle constitutes the inlet section of the second airflow channel, and the outlet section of the airflow channel has a certain clamping distance with the central axis Angle; the inner wall part of the transition annular sleeve beyond the duty grade oil film nozzle constitutes the expansion section of the second airflow channel; The annular main fuel stage oil supply plate includes a main fuel stage layered partition arranged at its inner circumference, a main fuel stage oil chamber located on its back side, and a main fuel stage oil chamber located on its outer surface and communicating with the main fuel stage oil chamber The fuel injection hole of the main combustion stage; the axial swirler of the internal stage of the main combustion stage is arranged in the third airflow channel between the inlet section of the transition annular sleeve and the layered partition of the main combustion stage; the The outer stage radial swirler of the main combustion stage is arranged in the fourth airflow passage between the annular main combustion stage oil supply plate and the peripheral annular sleeve; The internal stage axial swirler of the main combustion stage and the radial swirler of the external stage of the main combustion stage are separated by the layered partition of the main combustion stage; the inner wall surface of the peripheral annular sleeve constitutes the main combustion stage stage premix channel. 2. The air atomizing fuel nozzle device according to claim 1, characterized in that: the rotation direction of the airflow of the inner-stage axial swirler of the duty level is the same as the rotation direction of the airflow of the outer-stage axial swirler of the duty level same or opposite. 3. The air atomizing fuel nozzle device according to claim 1, characterized in that: the airflow rotation direction of the inner axial swirler of the main combustion stage is the same as the airflow rotation direction of the outer axial swirler of the duty stage The same or opposite, the airflow rotation direction of the radial swirler at the outer stage of the main combustion stage is opposite to that of the axial swirler at the inner stage of the main combustion stage. 4. The air atomizing fuel nozzle device according to claim 1, characterized in that: the fuel injection hole of the main combustion stage is located downstream of the blade channel of the outer stage radial swirler of the main combustion stage, and the radial swirl flow of the outer stage of the main combustion stage The number of vane channels of the vane is an integral multiple of the number of fuel injection holes of the main combustion stage, and the fuel injection holes of the main combustion stage are evenly distributed along the circumference. 5. The air atomizing fuel nozzle device according to claim 1, characterized in that the diameter of the fuel injection hole of the main combustion stage is in the range of 0.4 mm to 1.2 mm. 6 . The air atomizing fuel nozzle device according to claim 1 , wherein the ratio of the radial height of the fuel injection hole of the main combustion stage to the radial height of the layered partition of the main combustion stage is in the range of 1.1 to 1.3. 7. The air atomizing fuel nozzle device according to claim 1, characterized in that: the ratio of the length of the main combustion stage layered partition to the main combustion stage fuel injection hole to the main combustion stage swirler outlet is in the range of 0 to 0.5 Inside. 8. The air atomizing fuel nozzle device according to claim 1, characterized in that: the unit gas volume of the central duty class accounts for 10%-20% of the total intake air volume of the combustion chamber, and the gas volume of the peripheral main combustion level units accounts for 10%-20% of the total intake air volume of the combustion chamber. 65%-75% of the gas volume, the gas volume of the axial swirler in the duty class accounts for 30%-70% of the gas volume in the duty class, and the gas volume of the axial swirler in the main combustion stage accounts for 20%- 80%. 9. The air atomizing fuel nozzle device according to claim 1, characterized in that: all the gas required for combustion enters from the head swirler, and there are no main combustion holes and mixing holes on the flame tube, only cooling holes .