CN112747334B - Combustion chamber head structure - Google Patents
Combustion chamber head structure Download PDFInfo
- Publication number
- CN112747334B CN112747334B CN202110077272.1A CN202110077272A CN112747334B CN 112747334 B CN112747334 B CN 112747334B CN 202110077272 A CN202110077272 A CN 202110077272A CN 112747334 B CN112747334 B CN 112747334B
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- channel
- splash plate
- swirler
- head structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 66
- 230000007704 transition Effects 0.000 claims abstract description 25
- 239000000446 fuel Substances 0.000 claims abstract description 21
- 230000001154 acute effect Effects 0.000 claims description 4
- 238000009826 distribution Methods 0.000 claims description 3
- 238000009827 uniform distribution Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 40
- 239000000295 fuel oil Substances 0.000 description 11
- 238000001816 cooling Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 239000000306 component Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- 238000010793 Steam injection (oil industry) Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Classifications
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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
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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
-
- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
本发明涉及燃烧室头部结构，包括旋流器组件和挡溅盘；旋流器组件和挡溅盘组成扇形燃烧室单元，若干个扇形燃烧室单元组成环形燃烧室；旋流器组件位于燃烧室单元扇形区域的中心位置，旋流器组件由第一供油系统、一级旋流器、二级旋流器和文氏管组成；挡溅盘连接旋流器组件的外周并与内环火焰筒和外环火焰筒相连；所述挡溅盘外侧设有第二供油系统，挡溅盘内部设有燃油的外侧通道、过渡通道、内侧通道、出油孔以及空气孔。本发明的有益效果是：本发明通过挡溅盘内部的外侧通道、过渡通道以及内侧通道的引流，促进主路燃油在旋流器组件外侧周向均匀分布，通过出油孔的均匀分布可以提升主路燃烧出油均匀性，避免主燃级局部燃烧热点的出现。
The present invention relates to a combustion chamber head structure, including 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 located at the center of the fan-shaped area of the combustion chamber unit, and the swirler assembly is composed of a first oil supply system, a primary swirler, a secondary swirler and a venturi; the splash plate is connected to the periphery of the swirler assembly and is connected to an inner ring flame tube and an outer ring flame tube; a second oil supply system is provided on the outer side of the splash plate, and an outer channel, a transition channel, an inner channel, an oil outlet hole and an air hole for the fuel are provided inside the splash plate. The beneficial effects of the present invention are as follows: the present invention promotes the uniform distribution of the main fuel in the circumferential direction of the outer side of the swirler assembly through the drainage of the outer channel, the transition channel and the inner channel inside the splash plate, and the uniform distribution of the oil outlet holes can improve the uniformity of the main combustion oil output, and avoid the occurrence of local combustion hot spots in the main combustion stage.
Description
Technical Field
The invention relates to a combustion chamber head structure, and belongs to the field of aeroengines and gas turbines.
Background
The aeroengine is a heart of an aircraft, is not only a power source for the aircraft to fly, 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 has higher and higher thrust-weight ratio requirement on the engine, the cycle parameters of the engine are continuously improved, the total increase ratio is more than 40, and the inlet and outlet temperature rise of the combustion chamber is more than 1100K.
The combustion chamber is the core component of the engine for converting chemical energy in the fuel into thermal energy. The increase of the inlet and outlet temperature rise of the combustion chamber tends to increase the gas-oil ratio of the combustion chamber. The combustion chamber is in a high-temperature, high-pressure and high-stress environment for a long time, and the increase of the oil-gas ratio is extremely easy to cause the faults of deflector ablation, head wall ablation and the like, so that the engine is difficult to work normally.
The high-temperature fuel gas generated in the combustion process of the fuel oil can damage and ablate the wall surface of the head of the combustion chamber, so that the temperature of the wall surface of the head of the combustion chamber is very important. At present, the conventional implementation mainly realizes wall cooling through setting up the guide plate to control the form that the cooling air current flows, but the guide plate is located the main combustion area generally, and combustion temperature is very high, damages the guide plate easily, and the cooling effect is relatively poor, and the cost is higher. Conventional art as shown in fig. 4, the combustion chamber includes a combustion chamber head 101, a liner 102, and a baffle 103.
The patent CN109899831A sets up the fuel cavity through setting up on the splash guard, sets up the oil outlet in sleeve position, not only can cancel the guide plate, can also reduce the splash guard temperature through the heat absorption vaporization heat absorption of fuel. However, the patent has the following problems that (1) the splash guard and the cyclone are integrally processed, the process difficulty and the processing cost are increased, (2) the cavity is not provided with any flow guiding and rectifying device, the fuel is easy to be unevenly distributed, the circumferential oil outlet of the oil outlet is further unevenly formed, local combustion hot spots are formed, and (3) the fuel entering the flame tube from the outlet hole can affect the fuel entering the flame tube from the nozzle 8, and two-stage flames mutually interfere. As shown in fig. 5, the burner comprises a combustion chamber 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.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a combustion chamber head structure.
The burner head structure comprises a cyclone assembly and a splash guard, wherein the cyclone assembly and the splash guard form a fan-shaped burner unit, a plurality of fan-shaped burner units form an annular burner, the cyclone assembly is located at the center of a fan-shaped area of the burner unit and comprises a first oil supply system, a primary cyclone, a secondary cyclone and a venturi, the splash guard is connected with the periphery of the cyclone assembly and is connected with an inner ring flame tube and an outer ring flame tube, a second oil supply system is arranged outside the splash guard, an outer side channel, a transition channel, an inner side channel, an oil outlet and an air hole of fuel are arranged inside the splash guard, the outer side channel is located at the edge position, far from the center, of the splash guard, the outer side channel is communicated with the second oil supply system, the inner side channel is located at the position, close to the center, of the splash guard, the inner side channel is provided with an oil outlet, the transition channel is located between the outer side channel and the inner side channel, the transition channel and the inner side channel are mutually communicated, the transition channel is arranged at the periphery of the inner side channel, the transition channel is provided with a certain angle relative to the inner side channel, and the inner side channel is provided with the air hole.
The cyclone assembly is characterized in that the center of the cyclone assembly is provided with a first oil supply system, a first-stage cyclone is arranged outside the first oil supply system, a second-stage cyclone is arranged outside the first-stage cyclone, and a venturi is arranged inside the first-stage cyclone.
Preferably the axial wall thickness of the splash guard is 2-4mm,
Preferably, the fuel passage inside the splash guard has an axial width of 1-3mm.
Preferably, the fan-shaped combustion chamber units are communicated with each other through an outer channel.
Preferably, a plurality of transition channels are arranged in each fan-shaped combustion chamber unit, and the distribution positions of the transition channels are in a central symmetry mode relative to the cyclone component.
Preferably, 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 two adjacent oil outlet holes is 5-36 degrees.
Preferably, the diameters of the air holes are 0.5-3mm, the air holes are uniformly distributed in the circumferential direction, and the interval between two adjacent air holes is 5-36 degrees.
Preferably, the air hole axis and the oil outlet hole axis form an acute angle.
Preferably, the number of the air holes and the oil outlet holes is in a multiple relation.
The beneficial effects of the invention are as follows:
1. According to the invention, through the drainage of the outer channel, the transition channel and the inner channel in the splash guard, the uniform distribution of the main fuel oil on the outer periphery of the cyclone component is promoted, and the uniformity of the main fuel oil can be improved through the uniform distribution of the oil outlet holes, so that the occurrence of local combustion hot spots of the main fuel stage is avoided.
2. According to the invention, the arrangement of the guide plate is canceled, the splash guard is positioned in a high-temperature area of the main combustion area, and through the arrangement of the fuel flow passage, the fuel in the cavity absorbs heat from the wall surface of the splash guard to raise the temperature and vaporize, and meanwhile, the temperature of the wall surface of the splash guard is reduced, so that the splash guard is prevented from being ablated.
3. The invention is provided with the air hole and the oil outlet, fuel steam is formed after the fuel oil of the main combustion stage is vaporized, the fuel steam and the air entering through the air hole are mutually mixed to form semi-premixed combustion, the combustion temperature is lower, the NO x emission is reduced, and the fuel oil and the air are respectively positioned at different outlets, so that the risk of tempering is avoided.
Drawings
FIG. 1 is a schematic longitudinal section of a fan-shaped combustion chamber unit;
FIG. 2 is a schematic view of section A-A of FIG. 1;
FIG. 3 is a schematic cross-sectional view of a full-ring combustor;
FIG. 4 is a schematic diagram of a conventional technical scheme;
Fig. 5 is a schematic structural diagram of an embodiment of patent CN109899831 a.
The reference numerals are 1, a cyclone assembly, 11, a first oil supply system, 12, a first-stage cyclone, 13, a venturi tube, 14, a second-stage cyclone, 15, a sleeve, 2, a splash guard, 21, a second oil supply system, 22, an outer channel, 23, a transition channel, 24, an inner channel, 25, an air hole, 26, an oil outlet, 3, an inner ring flame tube, 4 and an outer ring flame tube.
Detailed Description
The invention is further described below with reference to examples. The following examples are presented only to aid in the understanding of the invention. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.
As one embodiment, the combustion chamber head structure is characterized in that one part of air flow from the inlet of the combustion chamber enters the flame tube from the combustion chamber head, and the other part of air flow enters the flame tube from the openings on the inner ring flame tube 3 and the outer ring flame tube 4. Wherein air entering from the combustion chamber head enters the interior of the liner from the primary swirler 12, the secondary swirler 14 and the air holes 25, respectively. The combustion chamber head structure includes a swirler assembly 1 and a splash plate 2. The cyclone assembly 1 and the splash guard 2 form a sector-shaped combustion chamber unit, and a plurality of sector-shaped combustion chamber units form an annular combustion chamber. The swirler assembly 1 is positioned at the center of a fan-shaped area of the combustion chamber unit, and the splash guard 2 is connected with the periphery of the swirler assembly 1 and is connected with the inner ring flame tube 3 and the outer ring flame tube 4. The center of the cyclone assembly 1 is provided with a first oil supply system 11, a first-stage cyclone 12 is arranged outside the first oil supply system 11, a second-stage cyclone 14 is arranged outside the first-stage cyclone 12, a venturi 13 is arranged inside the first-stage cyclone, and the first oil supply system 11 and air flows flowing through the first-stage cyclone and the second-stage cyclone can form a precombustion-stage diffusion flame. The splash guard 2 is provided with a second oil supply system 21 on the outer side, an outer side channel 22, a transition channel 23, an inner side channel 24, an oil outlet 26 and an air hole 25 of fuel oil are arranged in the splash guard 2, the outer side channel 22 is positioned at the inner edge of the splash guard 2, the outer side of the outer side channel 22 is communicated with the second oil supply system 21, the inner side channel 24 is positioned in the splash guard 2 and close to the center, the inner side channel 24 is in a circular ring shape, the oil outlet 26 is arranged on one side, away from the head of a combustion chamber, of the inner side channel 24 for fuel oil steam injection, the transition channel 23 is arranged between the outer side channel 22 and the inner side channel 24 and used for connecting the outer side channel 22 and the inner side channel 24, the transition channel is arranged on the periphery of the inner side channel 24 in a fan blade shape, the transition channel 23 is at a certain angle relative to the inner side channel 24 and used for forming circumferential movement of the fuel oil so as to flow out of the oil outlet uniformly, the air hole 25 is arranged on the inner side of the inner side channel 24 and penetrates the splash guard 2, and air from the head of the combustion chamber can directly enter the flame tube through the air hole 25.
The outer channel 22, the transition channel 23 and the inner channel 24 form a carefully arranged cavity in the splash guard 2, and the fuel injected by the second fuel supply system 21 uniformly flows out of the oil outlet 26 through the outer channel 22, the transition channel 23 and the inner channel 24 in the splash guard 2, so that the formation of local hot spots in the combustion chamber is avoided as much as possible. Because the splash guard is positioned in the high-temperature area of the main combustion area, the fuel in the cavity can absorb the heat of the wall surface of the splash guard to vaporize, so that the surface temperature of the splash guard is reduced. The vaporized fuel oil has reduced density and viscosity, can form a main combustion stage semi-premixed flame with the air flowing out of the air holes, and meanwhile, the air holes 25 and the oil outlet 26 form an acute angle in the axial direction, so that the mutual blending between the air and the fuel oil steam can be enhanced, and the oil and gas mixture is more uniform. Not only reduces the combustion temperature and the emission of NO x, but also effectively avoids 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 cavity (fuel passage) in the splash plate 2 may be 1-3mm.
As a preferred embodiment, the outer channel 22 inside the splash guard is irregularly shaped, the outer side being in communication with the second oil supply system 21, and the different fan-shaped combustion chamber units being in communication with each other.
As a preferred embodiment, a plurality of transition passages may be arranged in a single sector-shaped combustion chamber unit, the distribution positions being in a centrosymmetric form with respect to the swirler assembly 1.
As a preferred embodiment, the diameter of the oil outlet 26 in the splash guard is 0.5-2mm, the oil outlet 26 is uniformly distributed in the circumferential direction, the distance between two adjacent oil outlets 26 is 5-36 degrees, the diameter of the air hole 25 is 0.5-3mm, the distance between two adjacent air holes 25 is 5-36 degrees, the axes of the air holes and the axes of the oil outlets are acute angles to enhance the mixing between fuel oil and air, and the number of the air holes and the number of the oil outlets are in a multiple relation.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110077272.1A CN112747334B (en) | 2021-01-20 | 2021-01-20 | Combustion chamber head structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110077272.1A CN112747334B (en) | 2021-01-20 | 2021-01-20 | Combustion chamber head structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112747334A CN112747334A (en) | 2021-05-04 |
| CN112747334B true CN112747334B (en) | 2025-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110077272.1A Active CN112747334B (en) | 2021-01-20 | 2021-01-20 | Combustion chamber head structure |
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| CN (1) | CN112747334B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114294676B (en) * | 2021-12-16 | 2023-05-12 | 北京动力机械研究所 | Pre-combustion chamber structure with wide ignition boundary |
| CN114413284A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Special-shaped swirler matched with head of annular combustion chamber |
| CN115183277B (en) * | 2022-06-02 | 2024-05-17 | 中国航发四川燃气涡轮研究院 | Flame tube |
| CN115597087B (en) * | 2022-08-12 | 2024-02-23 | 中国航发沈阳发动机研究所 | Hydrogen fuel combustion chamber head structure of expansion jet hole |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN214307199U (en) * | 2021-01-20 | 2021-09-28 | 浙江浙能技术研究院有限公司 | Head structure of combustion chamber |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4236378A (en) * | 1978-03-01 | 1980-12-02 | General Electric Company | Sectoral combustor for burning low-BTU fuel gas |
| DE102012002664A1 (en) * | 2012-02-10 | 2013-08-14 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenvormischbrenner |
| CN105042638B (en) * | 2015-06-25 | 2017-04-19 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN204961141U (en) * | 2015-07-08 | 2016-01-13 | 中国科学院工程热物理研究所 | Air atomizing fuel spray nozzle device |
| EP3118521A1 (en) * | 2015-07-13 | 2017-01-18 | Siemens Aktiengesellschaft | Burner for a gas turbine |
| CN108518248A (en) * | 2017-04-15 | 2018-09-11 | 罗显平 | A kind of screwed pipe rotor helical-screw paddle motor |
| CN109084330A (en) * | 2018-07-09 | 2018-12-25 | 西北工业大学 | The loopful combustion chamber that a kind of pass cyclone and pass eddy flow type are constituted |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN214307199U (en) * | 2021-01-20 | 2021-09-28 | 浙江浙能技术研究院有限公司 | Head structure of combustion chamber |
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| CN112747334A (en) | 2021-05-04 |
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