Two-stage spray cyclone integrated with fuel nozzle

Abstract

The utility model discloses a two-stage spray cyclone integrated with a fuel nozzle. The two-stage spray cyclone comprises an outer ring body, a middle ring body, an inner ring body, a plurality of clockwise guide vanes and a plurality of anticlockwise guide vanes, an annular first-stage rotational flow space is formed between the inner ring body and the middle ring body, an annular second-stage rotational flow space is formed between the middle ring body and the outer ring body, and a middle shaft area is formed in the inner ring body; the clockwise guide vane is mounted in one of the first-stage rotational flow space and the second-stage rotational flow space, and the anticlockwise guide vane is mounted in the other rotational flow space without the clockwise guide vane; a plurality of oil spraying holes are respectively distributed on the inner sides of the outer ring body and the middle ring body, and a plurality of oil spraying holes are distributed on the inner side of the inner ring body and / or an oil spraying nozzle is arranged at the rear part of the middle shaft area. The oil spraying device has the advantages that oil is sprayed in a layered mode from inside to outside and combined with reverse rotational flow, the oil spraying range is remarkably enlarged, atomization of sprayed oil and full and even mixing of the sprayed oil and air are better facilitated, and the energy conversion efficiency of fuel oil can be improved.

Description

Technical Field

[0001] The utility model relates to a two-stage spray swirler integrated with a fuel nozzle, belonging to the technical field of aviation gas turbine engines. Background Art

[0002] The swirler is an important component of the combustion chamber of an aircraft gas turbine, and its working performance comprehensively affects the comprehensive performance of the combustion chamber. The main functions of the swirler are: first, it generates a high-speed rotating jet at the head of the flame tube to form a low-pressure area, thereby creating a combustion recirculation area to ensure flame stability; second, the high-speed rotating jet of the swirler can increase the relative speed of the airflow and the oil droplets, thereby fully atomizing the fuel and forming an oil-mist mixture, which is conducive to improving combustion efficiency.

[0003] Swirls can be divided into two categories, namely, single-stage swirlers and double-stage swirlers. In most cases, single-stage swirlers are used in combustion chambers, but in order to adapt to the head design of high-temperature rise and large heat load combustion chambers, that is, to ensure that the air flow at the head has sufficient recirculation area and good aerodynamic atomization performance, double-stage axial flow swirlers are also used in combustion chambers.

[0004] When the combustion chamber is working, the fuel is sprayed into the combustion chamber through the nozzle. The spray angle of the nozzle is usually below 80°. When the swirler or the combustion chamber is large, the spray boundary covers a smaller area, and there is still a large distance between the spray boundary and the combustion chamber wall. The air in this area cannot be well mixed with the fuel spray and cannot participate in combustion, which affects the combustion performance.

[0005] In order to prevent the problem of poor mixing of air and spray in the flame tube head area, the traditional countermeasures are:

[0006] a) Reduce the air passage area of ​​the cyclone;

[0007] b) Reduce the cross-sectional area of ​​the flame tube;

[0008] c) Increase the spray angle of the fuel nozzle.

[0009] However, the above measures have the following shortcomings:

[0010] 1. It is not conducive to forming a large-scale, stable low-pressure reflux zone;

[0011] 2. It is difficult to properly match the spray cone angle of the fuel nozzle with the fuel injection pressure;

[0012] 3. Reduce the combustion efficiency of the combustion chamber.

[0013] The present application aims to solve the above-mentioned problems.

[0014] In order to be more targeted in solving the above problems, we conducted relevant searches and obtained a patent document with application number 202010569958.8 that is weakly related to the present application: This document discloses a filamentary arc plasma exciter based on a swirl hole, and the inner plasma cyclone and the outer cyclone adopt a split structure. A plurality of swirl holes are evenly distributed on the inner plasma cyclone shell. 2 to 5 electrodes are respectively installed in the swirl holes through the electrode mounting seat, and the circumference of the inner plasma cyclone shell is divided into n arc segments of equal length. The outer cyclone is installed on the upper end surface of the inner plasma cyclone. As a kind of plasma, filamentary arc discharge has great advantages in ignition and combustion in the combustion chamber of aircraft engines. The plasma exciter is combined with the combustion chamber head to realize the integration of ignition and combustion, and at the same time facilitate the mixing of active particles generated by plasma discharge and fuel molecules. The present invention overcomes the disadvantage that the sliding arc plasma cannot discharge when the inlet air flow is 0, improves the combustion efficiency, has a simple structure, and does not require the establishment of a special air supply system and fuel supply system. Although the application provides a plurality of swirl holes on the inner plasma cyclone shell, when the cyclone or the combustion chamber is larger, the spray boundary coverage area is still small, and there is still a large distance between the spray boundary and the combustion chamber wall. The air in this area still cannot be fully mixed with the fuel spray. Utility Model Content

[0015] The technical problem to be solved by the utility model is: how to form a spray boundary coverage area of ​​a larger range and enable the oil mist to be fully atomized and fully mixed with the airflow.

[0016] In view of the above problems, the technical solution proposed by the utility model is:

[0017] A two-stage spray swirler with an integrated fuel nozzle comprises an outer ring body, a middle ring body, an inner ring body, a plurality of clockwise guide vanes, and a plurality of counterclockwise guide vanes; an annular primary swirling space is between the inner ring body and the middle ring body, an annular secondary swirling space is between the middle ring body and the outer ring body, and the inner ring body is a central axis area; the clockwise guide vanes are installed in one of the primary swirling space and the secondary swirling space, and the counterclockwise guide vanes are installed in the other swirling space where the clockwise guide vanes are not installed; a plurality of fuel injection holes are arranged on the inner side of the outer ring body and the middle ring body, a plurality of fuel injection holes are arranged on the inner side of the inner ring body, and / or a fuel injection nozzle is arranged at the rear of the central axis area.

[0018] Furthermore, the outer ring body and the middle ring body are respectively provided with an annular outer ring cavity and a middle ring cavity for supplying fuel, and the fuel injection holes on the outer ring body and the fuel injection holes on the middle ring body are respectively connected to the outer ring cavity and the middle ring cavity.

[0019] Furthermore, a counterclockwise guide vane is arranged in the secondary swirl space, and among the multiple counterclockwise guide vanes, at least one counterclockwise guide vane is provided with a second connecting flow channel connecting the outer ring cavity and the middle ring cavity.

[0020] Furthermore, the inner ring body is provided with an annular inner ring cavity for supplying fuel, and the fuel injection holes on the inner ring body are communicated with the inner ring cavity.

[0021] Furthermore, a clockwise guide vane is arranged in the first-level swirl space, and among the multiple clockwise guide vanes, at least one clockwise guide vane is provided with a connecting flow channel 1 connecting the middle ring cavity and the inner ring cavity.

[0022] Furthermore, it also includes an external oil supply pipe, which is connected to any one of the outer ring cavity, the middle ring cavity and the inner ring cavity. Beneficial Effects

[0023] The layered fuel injection from the inside to the outside combined with the reverse swirl significantly expands the range of fuel injection, is more conducive to the atomization of the fuel injection and its full mixing with the air, and can improve the energy conversion efficiency of the fuel. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a three-dimensional schematic diagram of the two-stage spray cyclone described in Example 1;

[0025] Figure 2 It is a cross-sectional schematic diagram of the two-stage spray cyclone described in Example 1;

[0026] Figure 3 It is a cross-sectional schematic diagram of the two-stage spray cyclone described in Example 2;

[0027] Figure 4 This is a cross-sectional schematic diagram of the two-stage spray cyclone described in Example 3.

[0028] In the figure: 1. outer ring body; 101. outer ring cavity; 2. middle ring body; 201. middle ring cavity; 3. inner ring body; 301. inner ring cavity; 4. clockwise guide vane; 5. counterclockwise guide vane; 6. primary swirl space; 7. secondary swirl space; 8. central axis area; 9. fuel injection hole; 10. connecting flow channel one; 11. connecting flow channel two; 12. external fuel supply pipe; 13. fuel injection nozzle. DETAILED DESCRIPTION

[0029] The utility model is further described below in conjunction with the accompanying drawings: Embodiment 1

[0030] like Figure 1As shown in FIG. 2, a two-stage spray swirler with an integrated fuel nozzle comprises an outer ring body 1, a middle ring body 2, an inner ring body 3, a plurality of clockwise guide vanes 4, and a plurality of counterclockwise guide vanes 5; between the inner ring body 3 and the middle ring body 2 is an annular primary swirling space 6, between the middle ring body 2 and the outer ring body 1 is an annular secondary swirling space 7, and inside the inner ring body 3 is a central axis area 8; the clockwise guide vanes 4 are installed in one of the primary swirling space 6 and the secondary swirling space 7, and the counterclockwise guide vanes 5 are installed in the other swirling space where the clockwise guide vanes 4 are not installed. The improvement is that: a plurality of oil injection holes 9 are arranged on the inner side of the outer ring body 1 and the middle ring body 2, respectively, and a plurality of oil injection holes 9 are also arranged on the inner side of the inner ring body 3. When in use, the oil injection holes 9 arranged on the inner side of the inner ring body 3 spray oil to the central axis area 8, and ignition is ignited in the central axis area to form a stable low-pressure reflux area that is not blown out by the swirling gas. The fuel injection holes 9 arranged on the inner side of the outer ring body 1 and the fuel injection holes 9 arranged on the inner side of the middle ring body 2 respectively spray fuel into the primary swirl space 6 and the secondary swirl space 7. In this way, compared with the prior art which only relies on the fuel injection nozzle 13 arranged at the rear part of the central axis area to spray fuel, the range of fuel injection is significantly expanded, which is beneficial to the atomization and sufficient mixing of the fuel injection, and greatly improves the energy conversion efficiency of the fuel.

[0031] An annular outer ring cavity 101 and a middle ring cavity 201 for supplying fuel are respectively provided in the outer ring body 1 and the middle ring body 2. The fuel injection holes 9 on the outer ring body 1 and the fuel injection holes 9 on the middle ring body 2 are respectively connected to the outer ring cavity 101 and the middle ring cavity 201, thereby solving the fuel supply problem of the fuel injection holes 9 on the outer ring body 1 and the fuel injection holes 9 on the middle ring body 2.

[0032] Counterclockwise guide vanes 5 are arranged in the secondary swirl space 7 . Among the multiple counterclockwise guide vanes 5 , at least one counterclockwise guide vane 5 is provided with a connecting flow channel 11 connecting the outer ring cavity 101 and the middle ring cavity 201 .

[0033] An annular inner ring cavity 301 for supplying fuel is provided in the inner ring body 3 , and the fuel injection holes 9 on the inner ring body 3 are connected to the inner ring cavity 301 , thereby solving the fuel supply problem of the fuel injection holes 9 on the inner ring body 3 .

[0034] A clockwise guide vane 4 is arranged in the primary swirl space 6. Among the multiple clockwise guide vanes 4, at least one clockwise guide vane 4 is provided with a connecting flow channel 11 connecting the middle annular cavity 201 and the inner annular cavity 301.

[0035] It also includes an external oil supply pipe 12 , which is connected to any one of the outer ring cavity 101 , the middle ring cavity 201 and the inner ring cavity 301 . Embodiment 2

[0036] like Figure 3As shown, the difference from the first embodiment is that no injection hole 9 is provided on the inner ring body 3, and only an injection nozzle 13 is provided at the rear of the central axis area, and the injection nozzle 13 is mainly used to supply fuel for combustion in the low-pressure reflux area. Embodiment 3

[0037] like Figure 4 As shown, the difference from the first and second embodiments is that while the fuel injection hole 9 is provided on the inner ring body 3, a fuel injection nozzle 13 is provided at the rear of the central axis area, and the fuel injection nozzle 13 and the fuel injection hole 9 provided on the inner ring body 3 provide fuel for combustion in the low-pressure reflux area.

[0038] The above embodiments are only used to more clearly describe the present invention and cannot be regarded as limiting the protection scope of the present invention. Any modifications in equivalent forms should be regarded as falling within the protection scope of the present invention.

Claims

1. A two-stage spray swirler with an integrated fuel nozzle, comprising an outer ring body (1), a middle ring body (2), an inner ring body (3), a plurality of clockwise guide blades (4), and a plurality of counterclockwise guide blades (5); an annular primary swirling space (6) is provided between the inner ring body (3) and the middle ring body (2), an annular secondary swirling space (7) is provided between the middle ring body (2) and the outer ring body (1), and a central axis region (8) is provided within the inner ring body (3); the clockwise guide blades (4) are installed in one of the primary swirling space (6) and the secondary swirling space (7), and the counterclockwise guide blades (5) are installed in the other swirling space where the clockwise guide blades (4) are not installed; and the characteristics are as follows: A plurality of oil injection holes (9) are arranged on the inner sides of the outer ring body (1) and the middle ring body (2), respectively; a plurality of oil injection holes (9) are arranged on the inner side of the inner ring body (3) and / or an oil injection nozzle (13) is arranged at the rear of the middle axis region (8).

2. The double-stage spray swirler with integrated fuel nozzle according to claim 1, characterized in that: An outer ring cavity (101) and a middle ring cavity (201) for supplying fuel are respectively provided in the outer ring body (1) and the middle ring body (2); the fuel injection hole (9) on the outer ring body (1) and the fuel injection hole (9) on the middle ring body (2) are respectively connected to the outer ring cavity (101) and the middle ring cavity (201).

3. The double-stage spray swirler with integrated fuel nozzle according to claim 2, characterized in that: A counterclockwise guide blade (5) is arranged in the secondary swirl space (7), and among the plurality of counterclockwise guide blades (5), at least one counterclockwise guide blade (5) is provided with a second connecting flow channel (11) connecting the outer ring cavity (101) and the middle ring cavity (201).

4. The double-stage spray swirler with integrated fuel nozzle according to claim 2, characterized in that: An annular inner ring cavity (301) for supplying fuel is provided in the inner ring body (3), and a fuel injection hole (9) on the inner ring body (3) is communicated with the inner ring cavity (301).

5. The double-stage spray swirler with integrated fuel nozzle according to claim 4, characterized in that: A clockwise guide vane (4) is arranged in the primary swirl space (6), and among the multiple clockwise guide vanes (4), at least one clockwise guide vane (4) is provided with a connecting flow channel (10) connecting the middle ring cavity (201) and the inner ring cavity (301).

6. The double-stage spray swirler with integrated fuel nozzle according to claim 5, characterized in that: It also includes an external oil supply pipe (12), wherein the external oil supply pipe (12) is connected to any one of the outer ring cavity (101), the middle ring cavity (201) and the inner ring cavity (301).

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