CN113137638B - Double-stage axial swirler with concave cavity for strengthening oil-gas mixing and aero-engine - Google Patents

Double-stage axial swirler with concave cavity for strengthening oil-gas mixing and aero-engine Download PDF

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Publication number
CN113137638B
CN113137638B CN202110473905.0A CN202110473905A CN113137638B CN 113137638 B CN113137638 B CN 113137638B CN 202110473905 A CN202110473905 A CN 202110473905A CN 113137638 B CN113137638 B CN 113137638B
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swirler
sleeve
guide ring
cooling
gas
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CN113137638A (en
Inventor
王志凯
江立军
陈盛
彭中九
刘冉
刘逸博
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Hunan Aviation Powerplant Research Institute AECC
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Hunan Aviation Powerplant Research Institute AECC
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention discloses a double-stage axial swirler with a concave cavity for strengthening oil-gas mixing, which comprises a primary swirler and a secondary swirler, wherein a venturi tube is arranged between the primary swirler and the secondary swirler, a sleeve is arranged on the secondary swirler, and the primary swirler is sleeved on a central nozzle, and the double-stage axial swirler also comprises: the mixed flow part is arranged at the end part of the sleeve and is used for fully mixing oil gas in the combustion chamber again; the cooling portion, the cooling portion set up in on the sleeve, the cooling portion is used for carrying cooling gas and cools off the protection to combustion chamber swirler shell, has the vortex core Precession (PVC) of solving doublestage axial swirler flow field ubiquitous simultaneously and flows unstably, can cause the combustion instability and make combustion chamber flame stability reduce, is unfavorable for the effect of flame stabilization.

Description

Double-stage axial swirler with concave cavity for strengthening oil-gas mixing and aero-engine
Technical Field
The invention relates to the technical field of aviation gas turbine engine combustors, in particular to a double-stage axial swirler with a cavity for strengthening oil-gas mixing.
Background
The development of high-performance combustion chambers puts higher requirements on fuel atomization technology, and complete combustion needs to be realized in a shorter combustion area so as to shorten the length of the combustion chamber and reduce the weight of the combustion chamber; the concentration field of the main combustion area needs to be better organized to deal with the gas shortage caused by the high-temperature-rise combustion chamber used for adjusting the outlet temperature field; there is a need for higher required ignition performance, lean blow-out range, lower pollutant emissions, and the like.
The typical structure is represented by a CFM56 engine combustion chamber two-stage swirler, the fuel atomization device with the nozzle and the swirler can be flexibly designed according to the requirement of combustion performance, and the staged adjustment of fuel under different working conditions is realized, so that the required combustion chamber head airflow structure and fuel concentration distribution are obtained, and the good ignition performance, combustion performance and wide stable combustion range are ensured to be realized under a wide working state.
The existing two-stage axial swirler mainly comprises a first-stage swirler, a venturi, a second-stage swirler, a sleeve and the like. The existing two-stage axial swirler flow field generally has unstable swirl core Precession (PVC) flow, which can cause combustion instability and reduce flame stability of a combustion chamber, and is not favorable for flame stabilization.
In view of the above-mentioned drawbacks of the prior art, the present invention provides a dual-stage axial swirler with a cavity for enhanced oil-gas mixing.
Disclosure of Invention
The invention provides a double-stage axial swirler with a concave cavity for strengthening oil-gas mixing, which aims to solve the technical problems that swirl core Precession (PVC) flow is unstable, combustion instability is caused, flame stability of a combustion chamber is reduced, and flame stability is not facilitated in the flow field of the conventional double-stage axial swirler.
According to one aspect of the present invention, there is provided a dual stage axial swirler with cavity enhanced oil and gas blending, comprising: including one-level swirler and second grade swirler, one-level swirler with be provided with the venturi tube between the second grade swirler, be provided with the sleeve on the second grade swirler, on the central nozzle was located to one-level swirler cover, still included:
the mixed flow part is arranged at the end part of the sleeve and used for fully mixing oil gas in the combustion chamber, the mixed flow part is used for generating negative pressure so as to generate a backflow region and form a stable backflow region in the mixed flow part, and the PVC phenomenon which is easy to occur after the airflow of the primary swirler and the airflow of the secondary swirler at the two sides of the venturi tube and the fuel oil are subjected to shearing action is reduced;
the cooling part is arranged on the sleeve and used for conveying cooling gas and cooling and protecting the shell of the sleeve.
By adopting the technical scheme, the venturis with different structural characteristics such as different lengths and profiles are selected according to different combustion chamber requirements, fuel sprayed by the central nozzle impacts the profiles in the venturis to form pre-film atomization, and/or directly cuts and atomizes by airflow of the primary swirler and the secondary swirler without impacting any wall surface of the venturis, oil and gas are fully mixed by the flow mixing part on the sleeve, the uniformly mixed oil and gas are transferred into the combustion chamber for combustion, the swirler shell and the flow mixing part are cooled by the cooling part on the sleeve, the damage to the sleeve and the engine shell caused by overhigh temperature of the flowing fuel gas is avoided, the service lives of the combustion chamber and the swirler of the engine are prolonged, the air flows through the flow mixing part to expand suddenly after being close to the outer wall of the sleeve end part, the fluid on the inner side and the outer side is sucked, and then a negative pressure zone is generated at the flow mixing part, so as to generate gas backflow, the stable backflow area is formed in the mixed flow part, the PVC phenomenon which is easy to appear after the shearing action of the primary swirler and the secondary swirler air flow on the two sides of the venturi tube and fuel oil is effectively relieved or avoided through the simple cavity structure form, and the problems that the vortex core Precession (PVC) flow instability, the combustion instability and the combustion chamber flame stability reduction consequence are caused in the flow field of the two-stage axial swirler, and the flame stability is not facilitated are solved.
Further, mixed flow portion includes the guide ring, the guide ring sets up in telescopic tip, the guide ring inner wall with telescopic terminal surface is the contained angle setting and is formed with the concave cavity vortex, the concave cavity vortex is used for fully mixing the air of center nozzle spun fuel and first order swirler and second grade swirler transmission and carrying to the combustion chamber and burn.
By adopting the technical scheme, the concave cavity vortex is formed at the end part of the sleeve through the guide ring, fuel sprayed by the central nozzle impacts or does not impact on the inner wall surface of the venturi, oil mist is formed under the shearing action of airflow of the primary cyclone and the secondary cyclone, the oil mist passes through the concave cavity vortex at the tail end of the sleeve in the downstream movement process and temporarily stays in the concave cavity vortex, and the vortex in the concave cavity vortex enables the oil mist and air to be well mixed and then enters the downstream main combustion area. The air flows through the concave cavity vortex and is suddenly expanded after being close to the outer wall of the end part of the sleeve, fluid on the inner side and the outer side is sucked in an entrainment mode, and the concave cavity vortex is caused to be a negative pressure region, so that a backflow region is generated, a stable backflow region can be formed in the concave cavity vortex, the primary cyclones on the two sides of the venturi tube are effectively relieved or avoided through a simple structural form, the PVC phenomenon which is easy to occur after the airflow and fuel oil are subjected to shearing action is generated, the purposes of inhibiting combustion instability and reducing the noise of a combustion chamber are achieved, the concave cavity vortex has a flame stabilizing function on the basis of the flow stabilizing action, combustion flame can flow back to the insides of the cyclones in actual work, the insides of the concave cavity vortex are stable backflow regions, the concave cavity vortex can be ignited by tempering, the backflow regions formed in the concave cavity vortex can serve as stable ignition sources, and oil gas is fully used.
Further, the end of the guide ring is arc-shaped.
By adopting the technical scheme, the end part of the guide ring is arranged to be arc-shaped, the end part of the guide ring is prevented from being scratched when edges and corners lead to installation in the installation process, the liquid mist opening angle of the outlet of the swirler is increased, and the problems that the liquid mist concentration, the outlet temperature distribution coefficient (OTDF) is enlarged and the ignition is difficult due to the small liquid mist cone angle of the direct-injection double-stage axial swirler are solved.
Further, the terminal surface of guide ring is vertical setting.
Through adopting above-mentioned technical scheme, the tip of guide ring is vertical setting, and the guide ring is used with aeroengine's flame tube cooperation installation when the installation, and the vertical setting of tip through the guide ring has the effect of location installation, and increases swirler export liquid fog flare angle, has solved the liquid fog that the liquid fog cone angle that direct injection formula doublestage axial swirler exists is little and lead to and concentrated, export temperature distribution coefficient (OTDF) grow, and the difficult problem of igniteing.
Further, the end of the guide ring is provided with a chamfer facing the inner wall of the guide ring along the end face of the guide ring.
Through adopting above-mentioned technical scheme, can reduce the absorption of oil gas at the guide ring tip for the chamfer with the tip processing of guide ring, and through processing into the chamfer at the tip of guide ring, lightened aeroengine's weight when cooling the swirler shell, and through processing into the chamfer at the tip of guide ring when processing into the guide ring, convenient cutting process, and increase swirler export liquid fog field angle, it concentrates to have solved the liquid fog that the liquid fog cone angle that direct injection doublestage axial swirler exists is little and lead to, export temperature distribution coefficient (OTDF) grow, and the difficult problem of ignition.
Further, the included angle between the inner wall of the guide ring and the end face of the sleeve ranges from 90 degrees to 180 degrees, and the included angle includes 90 degrees but does not include 180 degrees.
Through adopting above-mentioned technical scheme, the inner wall with the guide ring sets up to 90-180 with the contained angle of sleeve tip, when mixing oil gas in the concave cavity vortex, the contained angle in concave cavity vortex is 90-180 can make things convenient for even oil gas that the mixing was accomplished to transmit to the flame tube combustion chamber and burn, and set up the contained angle in concave cavity vortex into 90-180, can be so that the sleeve tip is the slope setting, reduce telescopic weight, the effect that has lightweight design engine, and set up the contained angle in concave cavity vortex into 90-180, can increase the dwell time of oil gas in the concave cavity vortex, it burns in getting into low reaches main burning zone after the abundant mixing of oil gas in the concave cavity vortex.
Further, the length-to-height ratio of the cavity vortex is [1-2 ].
By adopting the technical scheme, the length-height ratio of the concave cavity vortex is set between 1-2, the problem that the oil-gas mixing effect is poor due to the fact that the inner wall of the guide ring is too short is avoided, an ideal backflow vortex structure is formed, the length-height ratio of the concave cavity vortex is set between 1-2, the problem that the guide ring occupies a large amount of space and weight in an engine due to the fact that the guide ring is too large is avoided, the aero-engine is applied to the aviation field, the requirement on the light weight of the engine is necessary, and the light weight of the engine is guaranteed while the stable work of the engine is guaranteed.
Furthermore, the cooling part comprises a first cooling channel, the first cooling channel is arranged in the sleeve, and the first cooling channel and the inner wall of the sleeve penetrate through the sleeve along the axial direction of the sleeve and penetrate out of the inner wall of the sleeve along the wall thickness direction at one end of the cavity vortex.
Through adopting above-mentioned technical scheme, transmit cooling gas to guide ring department through cooling channel one, form the protection gas film in the inner wall department of guide ring, when engine combustion work, protect the inner wall of guide ring and the shell of engine through the protection gas film, avoid the high temperature to lead to guide ring and swirler shell to damage the life who reduces guide ring and swirler.
Furthermore, the cooling portion further comprises a cooling ring, the cooling ring is arranged on the outer wall of the sleeve, a second cooling channel which is distributed along the axial direction is arranged in the inner wall of the cooling ring, a branch which penetrates out along the thickness direction of the wall of the cooling ring is arranged on the second cooling channel, and the branch is used for inputting cold air and is transmitted to the concave cavity vortex along the second cooling channel to cool the sleeve and the outer wall of the guide ring.
Through adopting above-mentioned technical scheme, through cooling channel two on the cooling ring, with cooling gas in cooling channel two is transmitted to cooling channel through the branch road, will cool off gas transmission to the inherent guide ring inner wall department of swirler and form the gas film through cooling channel two and protect the guide ring, the too high damage that causes guide ring and swirler outer wall of temperature when avoiding engine fuel to burn.
According to another aspect of the invention, there is provided an aircraft engine comprising a dual stage axial swirler with cavity enhanced oil and gas blending as described above.
By adopting the technical scheme, oil mist is formed by the shearing action of airflow of the primary cyclone 1 and the secondary cyclone 2, the oil mist passes through the concave cavity vortex 412 between the sleeve 4 and the guide ring 411 in the downstream movement process and temporarily resides in the concave cavity 412, the oil mist and air are well mixed by the vortex in the concave cavity 412 and enter a main combustion area in a form of uniformly mixed gas, the mixing and distribution of fuel oil at the outlet of the cyclone are favorably improved, the ignition performance of a combustion chamber is improved, and the temperature distribution of the outlet is improved; under the steady flow effect of the concave vortex 412, the vortex core Precession (PVC) phenomenon commonly existing at the outlet of the cyclone can be relieved or eliminated, and the combustion instability can be inhibited, and the combustion chamber noise can be reduced.
The invention has the following beneficial effects:
when fuel oil is combusted in a flame tube at the combustion chamber of the aero-engine, oil mist is formed through the shearing action of airflow of the primary cyclone and the secondary cyclone, the oil mist passes through a concave cavity vortex between the sleeve and the guide ring in the downstream movement process and temporarily resides in the concave cavity, the vortex in the concave cavity enables the oil mist and air to be well mixed and enter a main combustion area in a uniformly mixed gas mode, the mixing and distribution of the fuel oil at the outlet of the cyclone are favorably improved, the ignition performance of the combustion chamber is improved, and the temperature distribution of the outlet is improved; the vortex core Precession (PVC) phenomenon commonly existing at the outlet of the swirler can be relieved or eliminated by the flow stabilizing effect of the concave cavity vortex, the combustion instability can be inhibited, and the combustion chamber noise can be reduced.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view showing the overall structure of a preferred embodiment 1 of the present invention;
FIG. 2 is a schematic structural view of a guide ring according to preferred embodiment 1 of the present invention;
FIG. 3 is a schematic structural view of a guide ring according to preferred embodiment 2 of the present invention;
FIG. 4 is a schematic structural view of a guide ring according to the preferred embodiment 3 of the present invention;
fig. 5 is a schematic structural view of the cavity vortex of the preferred embodiment 4 of the present invention.
Illustration of the drawings:
1. a primary swirler; 2. a secondary cyclone; 3. a venturi; 4. a sleeve; 41. a mixed flow portion; 411. a guide ring; 412. a concave cavity vortex; 42. a cooling section; 421. a first cooling channel; 422. a cooling ring; 423. a second cooling channel; 424. and (4) branching.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
As shown in fig. 1 and 2, the embodiment discloses a two-stage axial cyclone with a cavity for enhancing oil-gas mixing, which includes a first-stage cyclone 1 and a second-stage cyclone 2, a venturi 3 is connected between the first-stage cyclone 1 and the second-stage cyclone 2, the end of the venturi 3 is arranged in a round angle, the end of the venturi 3 is machined into a round angle to reduce the adsorption of the venturi 3 on oil-gas, a central nozzle is arranged in the first-stage cyclone 1, the central nozzle forms oil mist through the shearing action of the air flow of the first-stage cyclone 1 and the second-stage cyclone 2 by injecting fuel oil, the oil mist passes through a cavity vortex 412 between a sleeve 4 and a guide ring 411 during the downstream movement process and temporarily resides in the cavity 412, and the vortex in the cavity 412 enables the oil mist and air to be well mixed, and the oil mist enter a main combustion area in a form of uniformly mixed fuel gas. The outer wall of the secondary cyclone 2 is further sleeved with a sleeve 4, the end portion of the sleeve 4 is provided with a mixed flow portion 41, the mixed flow portion 41 is used for fully mixing oil gas from the upstream, the sleeve 4 is further provided with a cooling portion 42, and the casing of the cyclone is cooled and protected through the cooling portion 42.
Referring to fig. 1 and 2, the flow mixing portion 41 is a guide ring 411, the guide ring 411 is integrally formed with the sleeve at the end of the sleeve, a recessed cavity vortex 412 is formed at the end of the guide ring 411 and the end of the sleeve 4, oil mist is formed by the shearing action of airflow of the primary cyclone 1 and the secondary cyclone 2, the oil mist passes through the recessed cavity 412 between the sleeve 4 and the guide ring 411 during the downstream movement process, the oil mist temporarily resides in the recessed cavity 412, and the vortex in the recessed cavity 412 enables the oil mist and air to be well mixed to enter the main combustion area for combustion in the form of uniformly mixed fuel gas. The length to height ratio of the cavity vortex 412 is 1.5, i.e. the ratio of the wall width of the guide ring 411 to the length of the side wall of the cavity vortex 412 on the sleeve 4 is 1.5. The length-height ratio of the concave cavity vortex 412 is set to be 1.5, so that the concave cavity vortex 412 has enough space for oil and gas mixing, and waste of fuel caused by insufficient oil and gas mixing is avoided. The tip processing of water conservancy diversion ring is the arc, through the arc setting of guide ring 411 tip, reduces oil gas and adsorbs on guide ring 411, still can increase the liquid fog cone angle, avoids the liquid fog to concentrate, improves export temperature distribution and promotes combustion chamber ignition performance.
Referring to fig. 1 and 2, the cooling portion 42 includes a first cooling channel 421 and a cooling ring 422, the first cooling channel 421 is disposed on the sleeve 4, the first cooling channel 421 is disposed on the inner wall of the sleeve 4 and penetrates through the inner wall of the sleeve 4, and one end of the guide ring 411 is bent to penetrate through the inner wall of the sleeve 4, and the inner wall of the sleeve 4 and the guide ring 411 are isolated from each other by inputting cooling gas into the cooling channel when the turbine engine works, so as to protect the sleeve 4 and the guide ring 411.
Referring to fig. 1 and 2, the cooling ring 422 is sleeved on the outer wall of the sleeve 4, a cooling channel II 423 is processed on the inner wall of the cooling ring 422, a branch 424 is processed on the cooling ring 422 along the wall thickness direction, cooling gas is transmitted on the branch 424, the cooling gas is transmitted into the cooling channel II 423, an insulating gas film is formed around the guide ring 411 through the cooling gas to insulate the temperature of the guide ring 411, and the service life of the guide ring 411 is prolonged. One end that two 423 of cooling channel are close to guide ring 411 becomes the horn mouth setting, set the gas outlet of two 423 of cooling channel into the horn mouth can effectually transmit cooling gas flow to guide ring 411 department and carry out the thermal insulation to guide ring 411 and handle, avoid the flame tube too high temperature to lead to guide ring 411 heat damage when burning, be the horn mouth setting through one side with two 423 of cooling channel towards guide ring 411, transmit the cooling gas in two of cooling channel to horn mouth department and form the gas film through the perisporium that the horn mouth will cool gas transmission at the guide ring through two of cooling channel, the too high temperature caused the damage to swirler outer wall and guide ring when reducing the engine burning.
The working principle of the double-stage axial swirler with the concave cavity for strengthening oil-gas mixing is as follows: when fuel oil is combusted in a flame tube at a combustion chamber of an aircraft engine, oil mist is formed through the shearing action of airflow of a primary cyclone 1 and a secondary cyclone 2, the oil mist passes through a concave cavity vortex 412 between a sleeve 4 and a guide ring 411 in the downstream movement process and temporarily stays in the concave cavity 412, the vortex in the concave cavity 412 enables the oil mist and air to be well mixed, and the oil mist and the air enter a main combustion area in a uniformly mixed gas mode, so that the mixing and distribution of the fuel oil at the outlet of the cyclone can be improved, the ignition performance of the combustion chamber can be improved, and the temperature distribution of the outlet can be improved; the flow stabilizing effect of the concave cavity vortex 412 can relieve or eliminate vortex core Precession (PVC) phenomenon commonly existing at the outlet of the swirler, so that the suppression of combustion instability and the reduction of combustion chamber noise are facilitated, cooling gas is input through the cooling channel I421 and the cooling channel I to generate gas film protection, when combustion is carried out in the flame tube, damage to the guide ring and the outer wall of the swirler due to overhigh temperature is avoided, and fuel can be introduced into the cooling channel I421 and the cooling channel II 423 to form the regenerative cooling concept swirler.
Example 2
Referring to fig. 3, the present embodiment is different from embodiment 1 in that the end of the guide ring 411 is vertically disposed, the guide ring 411 is installed in cooperation with a flame tube of an aircraft engine during installation, and the guide ring 411 is vertically disposed through the end of the guide ring 411, so that the present embodiment has an effect of positioning installation.
Example 3
Referring to fig. 4, the present embodiment is different from embodiment 1 in that the end of the guide ring 411 is processed to be chamfered, the chamfer processing on the end of the guide ring 411 can reduce the adsorption of oil gas to the end of the guide ring 411, the weight of the aircraft engine is reduced while the cyclone casing is cooled by processing the chamfer on the end of the guide ring 411, and the cutting processing is facilitated by processing the chamfer on the end of the guide ring 411.
Example 4
Referring to fig. 5, the present embodiment is different from embodiment 1 in that an angle between an inner wall of the guide ring 411 and an end of the sleeve 4 is 135 °, an angle between the inner wall of the guide ring 411 and the end of the sleeve 4 is 135 °, an angle between the guide ring 411 and the sleeve 4 is 135 °, so that oil gas mixed in the cavity vortex 412 can smoothly enter the flame tube for combustion, and the inclination between the guide ring 411 and the end of the sleeve 4 is set to reduce adsorption of the oil gas, increase residence time of mixed fuel oil and air, enhance mixing effect, and reduce the weight of the sleeve 4.
The embodiment also discloses an aircraft engine which comprises the concave cavity reinforced oil-gas mixing two-stage axial swirler, oil mist is formed through the shearing action of airflow of the primary swirler 1 and the secondary swirler 2, the oil mist passes through the concave cavity vortex 412 between the sleeve 4 and the guide ring 411 in the downstream movement process and temporarily stays in the concave cavity 412, the vortex in the concave cavity 412 enables the oil mist and air to be well mixed and enter a main combustion area in a uniformly mixed fuel gas mode, the mixing and distribution of fuel oil at the outlet of the swirler can be improved, and the ignition performance of a combustion chamber and the temperature distribution of the outlet can be improved; under the steady flow effect of the concave vortex 412, the vortex core Precession (PVC) phenomenon commonly existing at the outlet of the cyclone can be relieved or eliminated, and the combustion instability can be inhibited, and the combustion chamber noise can be reduced.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (9)

1. The utility model provides a cavity reinforces doublestage axial swirler of oil gas mixing, includes one-level swirler (1) and second grade swirler (2), be provided with venturi tube (3) between one-level swirler (1) and second grade swirler (2), be provided with sleeve (4) on second grade swirler (2), on central nozzle was located to one-level swirler (1) cover, its characterized in that: further comprising:
the mixed flow part (41) is arranged at the end part of the air outlet end of the sleeve (4), the mixed flow part (41) is used for fully mixing oil gas in the combustion chamber again, the mixed flow part (41) is used for generating negative pressure so as to generate a backflow region, and a stable backflow region is formed in the mixed flow part (41) so as to reduce the vortex core precession phenomenon after the shearing action of the airflow of the primary swirler (1) and the airflow of the secondary swirler (2) at the two sides of the venturi tube (3) and the fuel oil;
a cooling section (42), wherein the cooling section (42) is arranged on the sleeve (4), and the cooling section (42) is used for conveying cooling gas and cooling and protecting the shell of the sleeve (4);
mixed flow portion (41) include guide ring (411), guide ring (411) set up in the terminal surface of sleeve (4), guide ring (411) inner wall with the terminal surface of sleeve (4) is the contained angle setting and is formed with concave cavity vortex (412), concave cavity vortex (412) are used for carrying out abundant mixing and carrying to the combustion chamber main combustion area and burn to the air of center nozzle spun fuel and first grade swirler and second grade swirler transmission.
2. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the end face of the guide ring (411) is arranged in an arc shape.
3. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the end face of the guide ring (411) is vertically arranged.
4. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the end face of the guide ring (411) is provided with a chamfer from the end of the guide ring (411) towards the inner wall of the guide ring (411).
5. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the included angle between the inner wall of the guide ring (411) and the end face of the sleeve (4) ranges from 90 degrees to 180 degrees, and the included angle includes 90 degrees but does not include 180 degrees.
6. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the length-to-height ratio of the cavity vortex (412) is 1-2.
7. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the cooling portion (42) comprises a first cooling channel (421), the first cooling channel (421) is arranged in the sleeve (4), and the first cooling channel (421) and the inner wall of the sleeve penetrate through the sleeve in the axial direction of the sleeve and penetrate out of one end of the cavity vortex (412) along the wall thickness direction of the inner wall of the sleeve (4).
8. The dual stage axial swirler for cavity enhanced oil and gas blending of claim 1, wherein: the cooling portion (42) further comprises a cooling ring (422), the cooling ring (422) is arranged on the outer wall of the sleeve (4), a second cooling channel (423) which is distributed along the axial direction is arranged in the inner wall of the cooling ring (422), a branch (424) which penetrates out along the wall thickness direction of the cooling ring (422) is arranged on the second cooling channel (423), the branch (424) is used for inputting cold air and is transmitted to the concave cavity vortex (412) along the second cooling channel (423) to cool the outer wall of the sleeve (4) and the outer wall of the guide ring (411).
9. An aircraft engine comprising a dual stage axial swirler with cavity enhanced oil and gas blending as claimed in any one of claims 1 to 8.
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