CN214307199U - Head structure of combustion chamber - Google Patents
Head structure of combustion chamber Download PDFInfo
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- CN214307199U CN214307199U CN202120158071.XU CN202120158071U CN214307199U CN 214307199 U CN214307199 U CN 214307199U CN 202120158071 U CN202120158071 U CN 202120158071U CN 214307199 U CN214307199 U CN 214307199U
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- combustion chamber
- swirler
- channel
- head structure
- oil outlet
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Abstract
The utility model relates to a combustion chamber head structure, which comprises a swirler component and a splash shield; the swirler assembly and the splash plate form a fan-shaped combustion chamber unit, and a plurality of fan-shaped combustion chamber units form an annular combustion chamber; the swirler assembly is positioned at the center of the sector area of the combustion chamber unit and consists of a first oil supply system, a primary swirler, a secondary swirler and a venturi; the splash guard is connected with the periphery of the swirler assembly and connected with the inner ring flame tube and the outer ring flame tube; and a second oil supply system is arranged on the outer side of the splash guard, and an outer channel, a transition channel, an inner channel, an oil outlet and an air hole for fuel oil are arranged in the splash guard. The utility model has the advantages that: through the inside outside passageway of fender splash plate, the drainage of transition passageway and inboard passageway, promote main road fuel at swirler subassembly outside circumference evenly distributed, the evenly distributed through the oil outlet can promote main road combustion oil outlet homogeneity, avoids the appearance of main burning level local combustion hot spot.
Description
Technical Field
The utility model relates to a combustion chamber head structure belongs to aeroengine and gas turbine field.
Background
The aircraft engine is the heart of the aircraft, is not only a power source for the flight of the aircraft, but also an important driving force for promoting the development of aviation industry. In order to meet the combat requirement of high-speed maneuver, the modern high-performance fighter plane has higher and higher thrust-weight ratio requirement on an engine, the cycle parameter of the engine is also improved continuously, the total increase ratio reaches more than 40, and the temperature rise of an inlet and an outlet of a combustion chamber reaches more than 1100K.
The combustion chamber is a core component of the engine and is used for converting chemical energy in fuel oil into heat energy. The increase of the temperature rise of the inlet and the outlet of the combustion chamber will increase the oil-gas ratio of the combustion chamber. The combustion chamber is in a high-temperature, high-pressure and high-stress environment for a long time, faults such as guide plate ablation, head wall ablation and the like are easy to occur due to the increase of the oil-gas ratio, and the engine is directly difficult to work normally.
Because the high-temperature fuel gas generated in the combustion process of the fuel oil can damage and ablate the wall surface of the head part of the combustion chamber, the cooling of the wall surface of the head part of the combustion chamber is very important. At present, conventional embodiment is mainly through setting up the guide plate to the wall cooling is realized to the form that control cooling air flow flows, but, the guide plate generally is located the main combustion area, and combustion temperature is very high, damages the guide plate easily, and the cooling effect is relatively poor, and the cost is higher. Prior art solution as shown in fig. 4, the combustion chamber comprises a combustion chamber head 101, a flame tube 102 and a baffle 103.
Patent CN109899831A is through setting up the fuel cavity on the splash guard, sets up the oil outlet in the sleeve position, not only can cancel the guide plate, can also reduce the splash guard temperature through the fuel endothermic vaporization heat absorption. However, the patent has the following problems: (1) the splash guard and the swirler are integrally processed, so that the process difficulty and the processing cost are increased; (2) the cavity is not provided with any flow guide and rectifying device, so that fuel oil is easily distributed unevenly, further, the circumferential oil outlet of the oil outlet is uneven, and a local combustion hot spot is formed; (3) fuel entering the liner from the outlet orifice may have an effect on the fuel entering through the nozzle 8 and the two flames interfere with each other. As shown in fig. 5, includes: the burner comprises a burner head 1, a flame tube 2, a splash plate 3, a cavity 31, a first-stage oil supply system 4, an oil outlet 5, a first-stage swirler 6, a second-stage swirler 7 and a nozzle 8.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the not enough among the prior art, provide a combustion chamber head structure.
The combustor head structure comprises a swirler assembly and a splash plate; the swirler assembly and the splash plate form a fan-shaped combustion chamber unit, and a plurality of fan-shaped combustion chamber units form an annular combustion chamber; the swirler assembly is positioned at the center of the sector area of the combustion chamber unit and consists of a first oil supply system, a primary swirler, a secondary swirler and a venturi; the splash guard is connected with the periphery of the swirler assembly and connected with the inner ring flame tube and the outer ring flame tube; a second oil supply system is arranged on the outer side of the splash guard, and an outer channel, a transition channel, an inner channel, an oil outlet and an air hole for fuel oil are arranged in the splash guard; the outer channel is positioned at the edge position far away from the center in the splash guard, and the outer side of the outer channel is communicated with the second oil supply system; the inner side channel is positioned in the splash guard and close to the center, the inner side channel is of an annular structure, and an oil outlet hole is formed in one side of the inner side channel, which is far away from the head of the combustion chamber; the transition channel is arranged between the outer side channel and the inner side channel, the outer side channel, the transition channel and the inner side channel are communicated with each other, the transition channel is arranged on the periphery of the inner side channel in a fan blade shape, and the transition channel has a certain angle relative to the inner side channel; the air hole is arranged at the inner side of the inner channel and penetrates through the splash plate.
Preferably, the method comprises the following steps: the center of the cyclone component is provided with a first oil supply system, the outer side of the first oil supply system is provided with a first-stage cyclone, the outer side of the first-stage cyclone is provided with a second-stage cyclone, and the inner part of the first-stage cyclone is provided with a venturi.
Preferably, the method comprises the following steps: the axial wall thickness of the splash plate is 2-4 mm.
Preferably, the method comprises the following steps: the axial width of the fuel channel inside the splash shield is 1-3 mm.
Preferably, the method comprises the following steps: the sector combustion chamber units are communicated with each other through an outer channel.
Preferably, the method comprises the following steps: a plurality of transition passages are arranged in each sector combustion chamber unit, and the distribution positions of the transition passages are in a central symmetry mode relative to the swirler assemblies.
Preferably, the method comprises the following steps: the diameter of the oil outlet holes is 0.5-2mm, the oil outlet holes are uniformly distributed in the circumferential direction, and the interval between every two adjacent oil outlet holes is 5-36 degrees.
Preferably, the method comprises the following steps: the diameter of the air holes is 0.5-3mm, the air holes are evenly distributed in the circumferential direction, and the interval between every two adjacent air holes is 5-36 degrees.
Preferably, the method comprises the following steps: the axis of the air hole and the axis of the oil outlet hole form an acute angle.
Preferably, the method comprises the following steps: the number of the air holes and the oil outlet holes is in a multiple relation.
The utility model has the advantages that:
1. the utility model discloses an inside outside passageway of splash guard, transition passageway and the drainage of inboard passageway promote the main road fuel at swirler subassembly outside circumference evenly distributed, and evenly distributed through the oil outlet can promote the main road homogeneity of producing oil that burns, avoids the appearance of main burning level local combustion hotspot.
2. The utility model discloses the setting of cancellation guide plate, splash guard are located main combustion area high temperature region, and through setting up the fuel runner, the fuel in the cavity rises the temperature vaporization from splash guard wall heat absorption, has reduced splash guard wall temperature simultaneously, prevents that splash guard from being ablated.
3. The utility model discloses set up air hole and oil outlet, formed fuel steam after the fuel vaporization of main burning level, mixed each other with the air that the air hole got into, formed half premix burning, combustion temperature is lower, NOxThe emission is reduced; and because the fuel and the air are respectively positioned at different outlets, the risk of backfire does not exist.
Drawings
FIG. 1 is a longitudinal cross-sectional schematic view of a sector combustor unit;
FIG. 2 is a schematic cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is a schematic cross-sectional view of a full-ring combustor;
FIG. 4 is a schematic structural diagram of a conventional prior art solution;
figure 5 is a schematic structural diagram of an embodiment of patent CN 109899831A.
Description of reference numerals: 1. a swirler assembly; 11. a first oil supply system; 12. a primary swirler; 13. a venturi; 14. a secondary cyclone; 15. a sleeve; 2. a splash plate; 21. a second oil supply system; 22. an outboard channel; 23. a transition passage; 24. an inboard channel; 25. an air hole; 26. an oil outlet hole; 3. an inner ring flame tube; 4. and an outer ring flame tube.
Detailed Description
The present invention will be further described with reference to the following examples. The following description of the embodiments is merely provided to aid in understanding the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.
In one embodiment, the combustion chamber head structure is that a part of airflow from the combustion chamber inlet enters the inner part of the flame tube from the combustion chamber head, and the other part of airflow enters the inner part of the flame tube from the openings on the inner ring flame tube 3 and the outer ring flame tube 4. The air introduced from the combustion chamber head enters the flame tube from the primary swirler 12, the secondary swirler 14, and the air holes 25, respectively. The combustor head structure includes a swirler assembly 1 and a splash plate 2. The swirler assembly 1 and the splash plate 2 form a fan-shaped combustion chamber unit, and a plurality of fan-shaped combustion chamber units form an annular combustion chamber. The swirler assembly 1 is located in the center of the sector area of the combustor unit, and the splash plate 2 is connected to the outer periphery of the swirler assembly 1 and connected to the inner ring flame tube 3 and the outer ring flame tube 4. The center of the swirler component 1 is provided with a first oil supply system 11, a first-stage swirler 12 is arranged outside the first oil supply system 11, a second-stage swirler 14 is arranged outside the first-stage swirler 12, a venturi 13 is arranged inside the first-stage swirler, and the first oil supply system 11 and the air flow of the first-stage swirler and the second-stage swirler can form pre-combustion stage diffusion flame. A second oil supply system 21 is arranged on the outer side of the splash guard 2, and an outer channel 22, a transition channel 23, an inner channel 24, an oil outlet 26 and an air hole 25 of fuel oil are arranged in the splash guard 2; the outer channel 22 is positioned at the inner edge of the splash plate 2, and the outer side of the outer channel 22 is communicated with the second oil supply system 21; the inner channel 24 is positioned in the splash guard 2 and close to the center, the inner channel 24 is annular, and one side of the inner channel 24, which is far away from the head of the combustion chamber, is provided with an oil outlet 26 for fuel steam injection; the transition passage 23 is arranged between the outer passage 22 and the inner passage 24 and used for connecting the outer passage 22 and the inner passage 24, the transition passage is arranged on the periphery of the inner passage 24 in a fan-blade shape, and the transition passage 23 has a certain angle relative to the inner passage 24 and is used for forming circumferential movement of fuel so as to uniformly flow out of the oil outlet hole; the air hole 25 is provided inside the inner passage 24 and penetrates the splash plate 2, and air from the head of the combustion chamber can directly enter the interior of the flame tube through the air hole 25.
The outer passage 22, the transition passage 23 and the inner passage 24 form a well-arranged cavity in the splash plate 2, and the fuel oil sprayed by the second oil supply system 21 passes through the outer side of the inner part of the splash plate 2The channels 22, the transition channels 23 and the inner channels 24 uniformly flow out of the oil outlet holes 26, and local hot spots in the combustion chamber are prevented from being formed as much as possible. Because the splash guard is positioned in the high-temperature area of the main combustion area, fuel in the cavity can absorb heat on the wall surface of the splash guard to be vaporized, and therefore the surface temperature of the splash guard is reduced. The density and viscosity of the vaporized fuel oil are reduced, main combustion stage semi-premixed flame can be formed with the air flowing out from the air holes, and meanwhile, because the axial directions of the air holes 25 and the oil outlet holes 26 form an acute angle, the mutual mixing between the air and the fuel oil steam can be enhanced, and the oil-gas mixing is more uniform. Not only reducing combustion temperature to reduce NOxDischarge and effectively avoid the tempering problem.
As a preferred embodiment, the wall thickness of the splash plate 2 may be 2-4mm, and the axial width of the hollow space (fuel passage) in the splash plate 2 is 1-3 mm.
In a preferred embodiment, the outer channel 22 inside the splash plate is irregular and communicates with the second oil supply system 21, and different sector combustion chamber units communicate with each other.
As a preferred embodiment, a plurality of transition passages may be arranged in a single sector combustor unit, distributed in a centrally symmetrical fashion with respect to the swirler assembly 1.
As a preferred embodiment, the oil outlet holes 26 in the splash plate have the diameter of 0.5-2mm and are uniformly distributed in the circumferential direction, and the interval between every two adjacent oil outlet holes 26 is 5-36 degrees; the diameters of the air holes 25 are 0.5-3mm, the air holes are uniformly distributed in the circumferential direction, and the interval between every two adjacent air holes 25 is 5-36 degrees; the axis of the air hole and the axis of the oil outlet hole form an acute angle so as to enhance the mixing of fuel oil and air; the number of the air holes and the oil outlet holes is in a multiple relation.
Claims (10)
1. A combustion chamber head structure characterized by: comprises a swirler assembly (1) and a splash plate (2); the cyclone component (1) and the splash plate (2) form a fan-shaped combustion chamber unit, and a plurality of fan-shaped combustion chamber units form an annular combustion chamber; the swirler assembly (1) is positioned at the center of a sector area of the combustion chamber unit, and the swirler assembly (1) consists of a first oil supply system (11), a primary swirler (12), a secondary swirler (14) and a venturi (13); the splash guard (2) is connected with the periphery of the swirler component (1) and is connected with the inner ring flame tube (3) and the outer ring flame tube (4); a second oil supply system (21) is arranged on the outer side of the splash plate (2), and an outer channel (22), a transition channel (23), an inner channel (24), an oil outlet (26) and an air hole (25) for fuel oil are arranged in the splash plate (2); the outer channel (22) is positioned at the edge position, far away from the center, in the splash plate (2), and the outer side of the outer channel (22) is communicated with the second oil supply system (21); the inner side channel (24) is positioned in the splash plate (2) and close to the center, the inner side channel (24) is of a circular structure, and an oil outlet (26) is formed in one side of the inner side channel (24) far away from the head of the combustion chamber; the transition channel (23) is arranged between the outer side channel (22) and the inner side channel (24), the outer side channel (22), the transition channel (23) and the inner side channel (24) are communicated with each other, the transition channel (23) is arranged on the periphery of the inner side channel (24) in a fan blade shape, and the transition channel (23) has a certain angle relative to the inner side channel (24); the air hole (25) is provided inside the inner passage (24), and the air hole (25) penetrates the splash plate (2).
2. The combustion chamber head structure as set forth in claim 1, wherein: the center of the swirler component (1) is provided with a first oil supply system (11), the outer side of the first oil supply system (11) is provided with a primary swirler (12), the outer side of the primary swirler (12) is provided with a secondary swirler (14), and the inner part of the primary swirler is provided with a venturi (13).
3. The combustion chamber head structure as set forth in claim 1, wherein: the axial wall thickness of the splash plate (2) is 2-4 mm.
4. The combustion chamber head structure as set forth in claim 1, wherein: the axial width of the fuel channel in the splash guard (2) is 1-3 mm.
5. The combustion chamber head structure as set forth in claim 1, wherein: the sector combustion chamber units are communicated with each other through an outer passage (22).
6. The combustion chamber head structure as set forth in claim 1, wherein: a plurality of transition passages (23) are arranged in each sector combustion chamber unit, and the distribution positions of the transition passages (23) are in a central symmetry mode relative to the swirler assemblies (1).
7. The combustion chamber head structure as set forth in claim 1, wherein: the diameter of the oil outlet holes (26) is 0.5-2mm, the oil outlet holes are uniformly distributed in the circumferential direction, and the interval between every two adjacent oil outlet holes (26) is 5-36 degrees.
8. The combustion chamber head structure as set forth in claim 1, wherein: the diameter of the air holes (25) is 0.5-3mm, the air holes are uniformly distributed in the circumferential direction, and the interval between two adjacent air holes (25) is 5-36 degrees.
9. The combustion chamber head structure as set forth in claim 1, wherein: the axis of the air hole and the axis of the oil outlet hole form an acute angle.
10. The combustion chamber head structure as set forth in claim 1, wherein: the number of the air holes and the oil outlet holes is in a multiple relation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120158071.XU CN214307199U (en) | 2021-01-20 | 2021-01-20 | Head structure of combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120158071.XU CN214307199U (en) | 2021-01-20 | 2021-01-20 | Head structure of combustion chamber |
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| Publication Number | Publication Date |
|---|---|
| CN214307199U true CN214307199U (en) | 2021-09-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120158071.XU Active CN214307199U (en) | 2021-01-20 | 2021-01-20 | Head structure of combustion chamber |
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| CN (1) | CN214307199U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114440261A (en) * | 2022-01-11 | 2022-05-06 | 中国人民解放军国防科技大学 | Supersonic partial premixing combustion device with low turbulence |
| CN115628465A (en) * | 2022-10-20 | 2023-01-20 | 西北工业大学 | Head structure suitable for high-temperature combustion chamber of aircraft engine |
-
2021
- 2021-01-20 CN CN202120158071.XU patent/CN214307199U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114440261A (en) * | 2022-01-11 | 2022-05-06 | 中国人民解放军国防科技大学 | Supersonic partial premixing combustion device with low turbulence |
| CN114440261B (en) * | 2022-01-11 | 2023-09-01 | 中国人民解放军国防科技大学 | Supersonic part premixed combustion device with low turbulence |
| CN115628465A (en) * | 2022-10-20 | 2023-01-20 | 西北工业大学 | Head structure suitable for high-temperature combustion chamber of aircraft engine |
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