CN109519970B - Double-stage axial swirler and aero-engine combustion chamber using same - Google Patents
Double-stage axial swirler and aero-engine combustion chamber using same Download PDFInfo
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- CN109519970B CN109519970B CN201811337870.2A CN201811337870A CN109519970B CN 109519970 B CN109519970 B CN 109519970B CN 201811337870 A CN201811337870 A CN 201811337870A CN 109519970 B CN109519970 B CN 109519970B
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- venturi tube
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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
- F23R3/02—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
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
Abstract
The invention discloses a two-stage axial swirler and an aero-engine combustion chamber using the same, the two-stage axial swirler comprises a venturi tube and a sleeve arranged around the periphery of the venturi tube, a nozzle mounting hole is formed in the center of the venturi tube, a first-stage swirler blade is arranged in the venturi tube, a second-stage swirler blade is arranged between the venturi tube and the sleeve, a plurality of tooth-shaped structures are uniformly distributed at an outlet section of the venturi tube along the circumferential direction of the venturi tube, a gap penetrating through the inner wall surface and the outer wall surface of the venturi tube is formed between every two adjacent tooth-shaped structures, and the gap is used for communicating air flow channels respectively positioned on the inner side and the outer side of the venturi tube, so that fluid of the two air flow channels. The invention can accelerate the fluid mixing efficiency of two airflow channels at the inner side and the outer side of the venturi, strengthen fuel oil atomization and oil-gas mixing and improve atomization performance; the ignition performance and the outlet temperature distribution of the combustion chamber are improved; the tooth-shaped structure also plays a role in restraining and damping the precession of the inner airflow vortex core for the airflow outside the venturi tube.
Description
Technical Field
The invention relates to the field of swirlers, in particular to a two-stage axial swirler and an aero-engine combustion chamber for trial use of the same.
Background
The two-stage swirler mainly has the following functions: firstly, high-speed rotating jet flow is generated at the head of the flame tube to form a low-pressure backflow area to stabilize flame; secondly, air required by fuel combustion is provided, and the proper fuel-air ratio of the main combustion area is controlled; and thirdly, atomization is assisted, and the mixing of fuel oil and air is promoted. Therefore, the design of the swirler directly influences the combustion efficiency, the ignition and extinction performance of the combustion chamber, the outlet temperature field of the combustion chamber, the pollution emission of the combustion chamber and other performances.
In the existing two-stage axial swirler structure, a first-stage swirler and a second-stage swirler are both vane type swirlers, a venturi is of an annular structure, an outlet is a straight section, and the length of the venturi is longer. After the swirler is matched with the central nozzle, a fuel oil fog cone ejected by the nozzle is firstly sputtered on the venturi tube to initially form a liquid film, and finally the liquid film is further sheared and atomized by high-speed rotational flow from the first-stage swirler and the second-stage swirler at the outlet of the venturi tube to form broken fuel oil liquid drops. By adopting the atomization mode, the air flow mixing rate of the primary vortex device and the secondary vortex device is too low, so that interaction, atomization and mixing of fuel oil from the primary vortex device and air from the secondary vortex device are not facilitated; the fuel droplets are restrained from diffusing at the downstream of the swirler due to the limitation of the venturi structure, so that the fuel droplets are intensively distributed near the central axis of the swirler, the outlet temperature distribution coefficient of the combustion chamber is too high, and the ignition performance of the combustion chamber is also deteriorated.
Disclosure of Invention
The invention provides a two-stage axial swirler and an aero-engine combustion chamber for trying the same, and aims to solve the technical problem that the ignition performance of the combustion chamber is influenced by the fact that the interaction, atomization and mixing of fuel oil and air of the swirler is limited by a straight structure of a venturi outlet of the existing two-stage axial swirler.
The technical scheme adopted by the invention is as follows:
the utility model provides a doublestage axial swirler, include venturi tube and enclose the sleeve of establishing in venturi tube periphery, the central authorities of venturi tube have the nozzle mounting hole, be provided with one-level swirler blade in the venturi tube, be equipped with second grade swirler blade between venturi tube and the sleeve, the export section of venturi tube has evenly laid a plurality of dentate structures along venturi tube circumference, have the breach that runs through venturi tube inner and outer wall between two adjacent dentate structures, the breach is used for the intercommunication to be located the air current passageway of venturi tube inside and outside respectively for the fluid of two air current passageways forms the flow direction vortex through breach department interact.
Further, the outlet section of the venturi tube is sequentially connected by a plurality of tooth-shaped structures to form an annular shape.
Further, the tooth-shaped structure is any one of a rectangular tooth shape, a triangular tooth shape, a trapezoidal tooth shape and an arc tooth shape.
Preferably, the outlet section of the venturi tube is uniformly distributed with 8 tooth-like structures.
Preferably, the extending direction of the tooth-shaped structure forms an included angle of 0 to +/-10 degrees with the central axis of the venturi tube.
Preferably, the length of the tooth-like structure in the axial direction is 4mm to 6 mm.
Preferably, the outlet portion of the sleeve flares outwardly away from the venturi; and the extending direction of the outlet part forms an included angle of 40-50 degrees with the central axis of the venturi tube.
Preferably, the outlet portion of the sleeve is uniformly provided with a plurality of tooth-shaped structures along the circumferential direction of the sleeve.
Preferably, the venturi, the first-stage swirler vanes and the nozzle mounting holes form a first-stage swirler, and the venturi, the sleeve and the second-stage swirler vanes form a second-stage swirler; the first stage swirler vanes rotate in the opposite direction to the second stage swirler vanes.
According to another aspect of the invention, an aircraft engine combustion chamber is also provided, which comprises a flame tube, the head of which is provided with the double-stage axial swirler.
The invention has the following beneficial effects:
according to the two-stage axial swirler, the plurality of tooth-shaped structures are uniformly distributed at the outlet section of the venturi along the circumferential direction of the venturi, and the gaps between the adjacent tooth-shaped structures can enable fluid in two airflow channels on the inner side and the outer side of the venturi to mutually act through the gaps to form a flow direction vortex, so that the mixing efficiency can be accelerated by the flow direction vortex, meanwhile, strong shearing force can be formed, disturbance to a liquid film formed on the venturi is increased, fuel oil atomization and oil-gas mixing are enhanced, the atomization performance is improved, and the spray quality is improved; secondly, the invention can enlarge the fuel spray cone angle ejected by the nozzle mounting hole by utilizing the venturi tube with the tooth-shaped structure, thereby achieving the purpose of improving the ignition performance and the temperature distribution of the outlet of the combustion chamber; moreover, the invention plays a role in inhibiting and damping the precession of the eddy core of the inner side airflow outside the venturi tube through the function of the tooth-shaped structure; in addition, the design of the notch enables the weight of the dual-stage axial swirler to be reduced.
The combustion chamber of the aero-engine adopts the venturi with the special structure, so that two rotational flows on the inner side and the outer side of the venturi can be mixed in advance, and the number of the rotational flows of the swirler is increased by forming flow direction vortexes at the notches between the adjacent tooth-shaped structures, so that the backflow strength of a backflow area is improved, and the stability of flame is improved.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural view of a dual-stage axial swirler of a preferred embodiment of the present invention;
FIG. 2 is a schematic diagram of the operating principle of a dual-stage axial swirler of a preferred embodiment of the present invention;
FIG. 3 is a schematic view from another angle in FIG. 2;
FIG. 4 is a schematic representation of the cross-sectional shape of the tooth-like structure of the present invention;
FIG. 5 is a schematic comparison of atomization performance test results for a dual stage axial swirler of the present invention and a conventional swirler;
FIG. 6 is a schematic diagram comparing the oil mist field of the dual-stage axial swirler of the present invention with that of a conventional swirler, wherein (a) is a schematic diagram showing the oil mist field formed for the dual-stage axial swirler of the present invention and (b) is a schematic diagram showing the oil mist field formed for the conventional swirler;
fig. 7 is a schematic diagram comparing the flow field test results of the dual-stage axial swirler of the present invention with that of a conventional swirler, wherein (a) is a schematic diagram showing the flow field of the dual-stage axial swirler of the present invention, and (b) is a schematic diagram showing the flow field of the conventional swirler.
The reference numbers illustrate:
1. a venturi; 10. a tooth-shaped structure; 11. a notch; 2. a sleeve; 3. a nozzle mounting hole; 4. a first stage swirler vane; 5. a secondary swirler vane; 6. a flow direction vortex; 7. a liquid film; 8. a reflux zone.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The invention designs a double-stage axial swirler with a tooth-shaped structure 10 at the outlet section of a venturi tube 1 on the basis of the design of the existing double-stage axial swirler, so that the pneumatic performance of the existing double-stage axial swirler is greatly improved by changing the mode of the interaction of air flows of the first-stage and second-stage axial swirlers of the existing double-stage axial swirler.
Referring to fig. 1 to 3, a preferred embodiment of the present invention provides a two-stage axial swirler, which includes a venturi tube 1 and a sleeve 2 surrounding the venturi tube 1, a nozzle mounting hole 3 is formed in the center of the venturi tube 1, a first-stage swirler vane 4 is disposed in the venturi tube 1, a second-stage swirler vane 5 is disposed between the venturi tube 1 and the sleeve 2, a plurality of tooth-shaped structures 10 are uniformly distributed at an outlet section of the venturi tube 1 along the circumferential direction of the venturi tube 1, a gap 11 penetrating through the inner and outer wall surfaces of the venturi tube 1 is formed between two adjacent tooth-shaped structures 10, and the gap 11 is used for communicating air flow channels respectively located at the inner side and the outer side of the venturi tube 1, so that fluid of the two air flow channels interacts at the gap 11 to form a flow-.
According to the two-stage axial swirler, the plurality of tooth-shaped structures 10 are uniformly distributed at the outlet section of the venturi tube 1 along the circumferential direction of the venturi tube, the gaps 11 between the adjacent tooth-shaped structures 10 can enable airflow/gas-liquid mixed flows of two airflow channels at the inner side and the outer side of the venturi tube 1 to form the flow-direction vortex 6 through interaction at the gaps 11, the flow-direction vortex 6 can accelerate mixing efficiency, meanwhile, strong shearing force can be formed, disturbance on a liquid film 7 formed on the venturi tube 1 is increased, fuel oil atomization and oil-gas mixing are enhanced, and therefore atomization performance is improved, and spray quality is improved; secondly, the venturi 1 with the tooth-shaped structure 10 can enlarge the fuel spray cone angle ejected from the nozzle mounting hole 3, so that the aims of improving the ignition performance and the temperature distribution of the outlet of the combustion chamber are fulfilled; moreover, the invention plays a role in inhibiting and damping the precession of the eddy core of the inner side airflow at the outer side of the venturi 1 through the function of the tooth-shaped structure 10; furthermore, the design of the notches 11 allows the weight of the dual stage axial swirler to be reduced.
In the invention, a venturi tube 1, a primary swirler vane 4 and a nozzle mounting hole 3 form a primary swirler, and the venturi tube 1, a sleeve 2 and a secondary swirler vane 5 form a secondary swirler. The dual stage axial swirler of the present invention operates to create a larger recirculation zone 8 downstream to stabilize the flame.
In the present invention, as shown in fig. 3, the direction of the air flow turning direction a of the primary swirler is opposite to the direction of the air flow turning direction B of the secondary swirler, and both adopt a vane type swirler structure. Specifically, the primary and secondary swirler vanes 4, 5 rotate in opposite directions. The invention facilitates the formation of a flow direction vortex 6 as shown in fig. 3 at each gap 11 by designing the two-stage swirler to have opposite directions of rotation, in cooperation with the gaps 11 between the tooth-like structures 10.
The venturi 1 as a whole tapers towards its central axis. The sleeve 2 is also overall tapered towards its central axis. Therefore, the air flow channels of the first-stage swirler and the second-stage swirler are both convergent channels. The nozzle mounting hole 3 is used for mounting and fixing a fuel nozzle.
Further, in the present invention, the venturi tube 1 has a front section in a contracted annular structure, and an outlet section is sequentially connected by a plurality of tooth-like structures 10 to form an annular structure. By adopting the structure, after the swirler is matched with the nozzle, the working principle of the swirler is as shown in fig. 2 and fig. 3, a fuel fog cone sprayed by the nozzle is firstly sputtered on the venturi tube 1 to preliminarily form a liquid film 7, and the liquid film is further cut and atomized by high-speed rotational flow from the first-stage swirler and the second-stage swirler at the outlet of the venturi tube 1 to form broken fuel droplet oil mist. In the invention, when the airflow of the primary vortex device and the airflow/gas-liquid mixed flow of the secondary vortex device pass through the outlet section of the venturi tube 1, a plurality of flow direction vortexes 6 are formed at the notches 11 of the tooth-shaped structure 10, and the strong shearing force formed by the flow direction vortexes 6 can increase the disturbance to the liquid film 7, so that the fuel atomization and the oil-gas mixing can be enhanced, the vortex core precession can be inhibited through the formed small vortexes, and the flame stabilization is facilitated.
Referring to fig. 4, the tooth structure 10 has any one of a rectangular tooth shape, a triangular tooth shape, a trapezoidal tooth shape, and a circular arc tooth shape. Wherein (a) is a sectional schematic view of a rectangular tooth profile, (b) is a sectional schematic view of a triangular tooth profile, (c) is a sectional schematic view of a trapezoidal tooth profile, and (d) is a sectional schematic view of an arc tooth profile. In the preferred embodiment, the tooth structure 10 has a trapezoidal tooth shape.
As shown in fig. 3, in the preferred embodiment, the outlet section of the venturi 1 is uniformly provided with 8 teeth 10. Of course, in other embodiments, the number of the tooth structures 10 may be changed as appropriate.
Furthermore, the extending direction of the tooth-shaped structure 10 forms an angle of 0 to +/-10 degrees with the central axis of the venturi 1. In the preferred embodiment, the included angle between the extending direction of the tooth-shaped structure 10 on the venturi tube 1 and the horizontal direction, i.e. the axial direction of the venturi tube 1, is 0 °, and the included angle can be designed within ± 10 °, so that the performance of the swirler can meet the requirements.
Further, the length of the tooth-like structure 10 in the axial direction is 4mm to 6 mm. The length dimension can be optimized according to the configuration of the swirler. In the preferred embodiment, the tooth 10 has an axial length of 6 mm.
Further, the outlet portion of the sleeve 2 of the present invention flares away from the venturi 1. And the extending direction of the outlet part forms an included angle of 40-50 degrees with the central axis of the venturi 1.
Optionally, the outlet portion of the sleeve 2 is uniformly distributed with a plurality of tooth-like structures along the circumference of the sleeve 2. The sleeve 2 is further provided with a tooth-shaped structure, so that the airflow mixing rate of the first-stage swirler and the second-stage swirler can be further enhanced, and meanwhile, the strength of precession instability of a swirl core of a flow field at the outlet of the swirler can be inhibited.
In the preferred embodiment, the spray cone angle of the nozzle spray is matched to the outlet section of the venturi 1 so that the fuel impinges just at the location of the tooth 10 of the venturi 1, i.e. the spray cone angle of the nozzle is 80 degrees.
The tooth-shaped structure 10 is applied to a two-stage axial swirler of an aero-engine combustion chamber, and the following effects can be realized:
1. improve the spraying quality. The invention forms strong shearing force formed by the flow direction vortex 6 through the dentate structure 10, and then improves the atomization performance by increasing the disturbance of the liquid film formed on the venturi 1, and the atomization performance of the invention and the atomization performance of the traditional swirler are shown in figure 5.
2. Improve the ignition performance of the combustion chamber and the temperature distribution at the outlet of the combustion chamber. As shown in fig. 6, the present invention can increase the spray cone angle by using the venturi 1 having such a tooth structure 10, thereby achieving the purpose of improving the ignition performance and the temperature distribution at the outlet of the combustion chamber.
3. The reflux intensity of reflux zone 8 is enhanced. The dual stage axial swirler of the present invention is used to create a large recirculation zone 8 downstream to stabilize the flame. Compared with the traditional swirler, the tooth-shaped structure 10 can mix the first-stage swirling flow and the second-stage swirling flow in advance, so that the swirling flow number of the double-stage axial swirler is increased, the backflow strength of a backflow area is improved, and the stability of flame is improved, as shown in fig. 7.
4. Inhibiting vortex core precession PVC at the outlet of the venturi 1. The traditional swirler can generate vortex core precession at the outlet of the venturi 1, unstable combustion and unfavorable flame stabilization are easily generated, and the invention enables the airflow of the secondary swirler to play the role of inhibiting and damping the vortex core precession of the primary swirler through the action of the tooth-shaped structure 10.
In a word, the two-stage axial swirler has relatively lighter weight, can greatly improve the fuel distribution and atomization performance at the outlet of the swirler, improve the backflow capacity of a backflow area, simultaneously inhibit the swirl core precession existing in the conventional swirler, improve the ignition performance of a combustion chamber, improve the outlet temperature distribution and flame stability and reduce the noise of the combustion chamber.
The invention also provides a combustion chamber which comprises a flame tube, wherein the head of the flame tube is provided with the double-stage axial swirler.
The combustion chamber of the aero-engine adopts the venturi 1 with the special structure, so that two rotational flows on the inner side and the outer side of the venturi 1 can be mixed in advance, the flow direction vortexes 6 are formed at the gaps 11 between the adjacent tooth-shaped structures 10, the number of the rotational flows of the swirler is increased (the number of the increased flow direction vortexes 6 is increased and corresponds to the number of the gaps 11), the backflow strength of a backflow area is improved, and the stability of flame is improved.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "horizontal", "vertical", and the like indicate orientations or positional relationships based on directions or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a designated orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
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. A double-stage axial swirler comprises a venturi tube (1) and a sleeve (2) surrounding the venturi tube (1), wherein a nozzle mounting hole (3) is formed in the center of the venturi tube (1), a first-stage swirler vane (4) is arranged in the venturi tube (1), and a second-stage swirler vane (5) is arranged between the venturi tube (1) and the sleeve (2),
a plurality of tooth-shaped structures (10) are uniformly distributed at the outlet section of the venturi tube (1) along the circumferential direction of the venturi tube (1), a notch (11) penetrating through the inner wall surface and the outer wall surface of the venturi tube (1) is formed between every two adjacent tooth-shaped structures (10), and the notches (11) are used for communicating air flow channels respectively positioned at the inner side and the outer side of the venturi tube (1), so that fluid of the two air flow channels mutually acts at the notches (11) to form a flow direction vortex (6);
the front section of the venturi tube (1) adopts a contracted annular structure, the outlet section is sequentially connected by a plurality of tooth-shaped structures (10) to form an annular shape, the rotating directions of the first-stage swirler vanes (4) and the second-stage swirler vanes (5) are opposite, and the gaps (11) between the tooth-shaped structures (10) are matched to be beneficial to forming a flow direction vortex (6) at each gap (11),
the outlet section of the venturi tube (1) is sequentially connected by a plurality of tooth-shaped structures (10) to form an annular shape.
2. The dual-stage axial swirler of claim 1,
the tooth-shaped structure (10) is in any one of a rectangular tooth shape, a triangular tooth shape, a trapezoidal tooth shape and an arc tooth shape.
3. The dual-stage axial swirler of claim 2, wherein,
the outlet section of the venturi tube (1) is uniformly provided with 8 tooth-shaped structures (10).
4. The dual-stage axial swirler of claim 1,
the included angle between the extension direction of the dentate structure (10) and the central axis of the venturi tube (1) is 0 degree to +/-10 degrees.
5. The dual-stage axial swirler of claim 1,
the length of the tooth-shaped structure (10) along the axial direction is 4-6 mm.
6. The dual-stage axial swirler of claim 1,
the outlet part of the sleeve (2) expands outwards in the direction away from the venturi tube (1); and the extending direction of the outlet part forms an included angle of 40-50 degrees with the central axis of the venturi tube (1).
7. The dual-stage axial swirler of claim 6,
the outlet part of the sleeve (2) is uniformly provided with a plurality of tooth-shaped structures along the circumferential direction of the sleeve (2).
8. The dual-stage axial swirler of claim 1,
the venturi tube (1), the primary swirler vanes (4) and the nozzle mounting holes (3) form a primary swirler, and the venturi tube (1), the sleeve (2) and the secondary swirler vanes (5) form a secondary swirler.
9. An aircraft engine combustion chamber comprising a flame tube, characterized in that the head of the flame tube is provided with a dual-stage axial swirler as claimed in any one of claims 1 to 8.
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| CN112177804B (en) * | 2020-09-16 | 2021-10-29 | 上海空间推进研究所 | Low-temperature engine suitable for space device |
| CN113137638B (en) * | 2021-04-29 | 2022-07-05 | 中国航发湖南动力机械研究所 | Double-stage axial swirler with concave cavity for strengthening oil-gas mixing and aero-engine |
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| CN202852880U (en) * | 2012-09-28 | 2013-04-03 | 中国航空动力机械研究所 | Double-stage radial swirler |
| CN103175219B (en) * | 2013-03-21 | 2014-12-17 | 哈尔滨工程大学 | Venturi tube device used for head portion of chemical regenerative cycle combustor |
| CN103335333B (en) * | 2013-06-21 | 2015-06-17 | 北京航空航天大学 | Single-oil passage pre-diaphragm type staggered plate primary combustion stage premixing and pre-vaporizing low-pollution combustor |
| CN204127993U (en) * | 2014-10-08 | 2015-01-28 | 中国科学院工程热物理研究所 | A kind of zigzag wall Venturi tube runner wall structure |
| FR3029271B1 (en) * | 2014-11-28 | 2019-06-21 | Safran Aircraft Engines | ANNULAR DEFLECTION WALL FOR TURBOMACHINE COMBUSTION CHAMBER INJECTION SYSTEM PROVIDING EXTENSIVE FUEL ATOMIZATION AREA |
| CN104676647A (en) * | 2014-12-15 | 2015-06-03 | 西北工业大学 | Venturi apparatus for strengthening liquid-membrane crushing effect |
| CN106705045B (en) * | 2017-01-22 | 2019-08-09 | 中国科学院工程热物理研究所 | A kind of adjustable nozzle of interior outer flow passage equivalent proportion, nozzle array and burner |
| CN108758691A (en) * | 2018-03-08 | 2018-11-06 | 西北工业大学 | A kind of expansion segment adds the Venturi tube of boss |
| CN108204604B (en) * | 2018-03-13 | 2023-05-23 | 中国航空发动机研究院 | Combustion chamber multi-stage swirl nozzle with periodically varying outlet structure |
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