CN115200038A - Afterburner adopting air-cooled serial support plate for rectification - Google Patents
Afterburner adopting air-cooled serial support plate for rectification Download PDFInfo
- Publication number
- CN115200038A CN115200038A CN202210863210.8A CN202210863210A CN115200038A CN 115200038 A CN115200038 A CN 115200038A CN 202210863210 A CN202210863210 A CN 202210863210A CN 115200038 A CN115200038 A CN 115200038A
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- Prior art keywords
- support plate
- afterburner
- rectification
- extension board
- air
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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
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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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The application belongs to the field of afterburner design, and relates to an afterburner adopting air-cooled serial support plates for rectification, which comprises a rectification system, an ignition combustion system and a vibration-proof system; the rectifying support plate comprises a front support plate, a rear support plate, an inner cone and a converging ring, and the rear support plate comprises a bending section and a flat section; the method comprises the following steps that the culvert airflow firstly passes between two adjacent front support plates, the front support plates have larger bending degree, the culvert airflow can be rectified at a larger angle, the airflow angle of the culvert airflow is greatly reduced after the culvert airflow is rectified in the front support plates, then the culvert airflow enters the bending section of the rear support plate to be rectified again, and the culvert airflow flows out along the straight section after the rectification is finished, so that tissue combustion is carried out; the flow area of the connotative airflow at the position of the rectification support plate is not greatly changed, and meanwhile, the whole length required by rectification is reduced, the weight is reduced, the length of the afterburner is reduced, and the weight of the afterburner is greatly reduced.
Description
Technical Field
The application belongs to the field of afterburner design, and particularly relates to an afterburner adopting air-cooled serial support plates for rectification.
Background
Certain type of airplane realizes acceleration and improves maneuvering characteristics by starting an aircraft engine to apply force. The future warplanes require that the aeroengine still has higher stress application performance and reliability under higher thermal load. The gas temperature of an aircraft engine is higher, the flow field is more complex, the temperature of a boosting inlet is as high as 1300K and exceeds the service temperature of high-temperature alloy, and meanwhile, the airflow angle of the inlet can reach more than 35 degrees, airflow rectification is required, and reliable ignition and stable combustion of a boosting combustion chamber are realized.
In the prior art, the rectification and stable combustion functions are unified by utilizing the rectification support plate, meanwhile, components such as a fuel main pipe and the like are placed inside the rectification support plate, and the rectification support plate, the fuel main pipe, an ignition electric nozzle and the like are cooled by utilizing bypass airflow, so that the reliable work of the afterburner is ensured.
In the prior art, a turbine rear support plate is adopted to rectify an inlet flow field of an afterburner. However, when the airflow angle at the inlet is large, the rectification effect is not ideal, and a large surplus swirl still exists in the afterburner, which affects the stable working characteristics of ignition, tissue combustion and the like of the afterburner, and meanwhile, the risk of oscillatory combustion still exists. If an ideal rectification effect is achieved, the length of the rear support plate needs to be increased, so that the length of the afterburner is lengthened, and the weight is greatly increased.
Therefore, how to reduce the length of the rectifying support plate and the length of the afterburner while ensuring the rectifying performance is a problem to be solved.
Disclosure of Invention
The application aims to provide an afterburner adopting air-cooled serial support plates for rectification, and the problem that the rectification effect is not ideal or the rectification can be effectively carried out but the length of the combustion chamber is long when rectification is carried out under a large-angle inlet airflow angle is solved.
The technical scheme of the application is as follows: the afterburner comprises a rectifying system and an ignition combustion system, wherein the rectifying support plate comprises a front support plate, a rear support plate, an inner cone and a converging ring, the front support plate and the rear support plate are uniformly arranged at intervals along the circumferential direction of the inner cone, the front support plate and the rear support plate are attached, the tail edge of the front support plate and the front edge of the rear support plate are arranged in a staggered mode, the rear support plate comprises a bending section and a flat section, the bending degree of the bending section is smaller than that of the front support plate, and a chamfer angle is formed in the tail edge of the front support plate.
Preferably, a first rectifying channel is formed between adjacent front support plates, a second rectifying channel communicated with the first rectifying channel is formed between adjacent bent and twisted sections, a group combustion channel communicated with the second rectifying channel is formed between adjacent straight sections, and the length of the group combustion channel is greater than that of the second rectifying channel.
Preferably, the front edge of the front support plate passes through the middle of the rear support plate along the extension line of the axial direction of the aircraft engine.
Preferably, an inner groove is formed in the position, corresponding to the tail edge of the front support plate, of the inner cone.
Preferably, the ignition combustion system comprises an oil spray rod, the oil spray rod is arranged inside the rear support plate, and an oil spray hole corresponding to the oil spray rod is formed in the rear edge of the rear support plate.
Preferably, the anti-vibration system is further included, the anti-vibration system comprises a diffuser outer wall and an anti-vibration heat shield, the diffuser outer wall is coaxially arranged on the outer side of the confluence ring, the anti-vibration heat shield comprises a horizontal heat shield and a wave heat shield which are coaxially connected, the length direction of the horizontal heat shield is arranged along the axis direction of the aircraft engine, the cross section of the wave heat shield is in a wave shape, and a gap is reserved between the horizontal heat shield and the rear support plate.
Preferably, a recirculation zone is formed between the rear support plate, the horizontal heat shield and the inner cone.
Preferably, a bypass cooling channel is arranged on the outer side of the flow combining ring, inner cavities communicated with the bypass cooling channel are formed in the front support plate and the rear support plate, first cooling holes communicated with the inner cavities are formed in the side walls of the front support plate and the rear support plate, the inner portion of the inner cone is communicated with the inner cavities, and second cooling holes communicated with the inner portion of the inner cone are formed in the side wall of the inner cone.
The afterburner adopting the air-cooled serial support plate for rectification comprises a rectification system, an ignition combustion system and a vibration-proof system; the rectification support plate comprises a front support plate, a rear support plate, an inner cone and a converging ring, and the rear support plate comprises a bending section and a flat section; the method comprises the following steps that the culvert airflow firstly passes between two adjacent front support plates, the front support plates have larger bending degree, the culvert airflow can be rectified at a larger angle, the airflow angle of the culvert airflow is greatly reduced after the culvert airflow is rectified in the front support plates, then the culvert airflow enters the bending section of the rear support plate to be rectified again, and the culvert airflow flows out along the straight section after the rectification is finished, so that tissue combustion is carried out; the flow area of the connotative airflow at the position of the rectification support plate is not greatly changed, and meanwhile, the whole length required by rectification is reduced, the weight is reduced, the length of the afterburner is reduced, and the weight of the afterburner is greatly reduced.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
FIG. 1 is a rear elevation view of the overall structure of the present application;
FIG. 2 is a schematic view of a connection structure of a front support plate and a rear support plate according to the present application;
FIG. 3 is a schematic view of the diffusion flow path of the afterburner of the present application.
1. A rear support plate; 2. a front support plate; 3. an inner cone; 4. a diffuser outer wall; 5. a converging ring; 6. a vibration-proof heat shield; 7. spraying an oil rod; 8. an inner groove; 9. a bending section; 10. a straight section; 11. a first rectifying channel; 12. a second rectifying channel; 13. a group combustion channel; 14. a horizontal heat shield; 15. a wave heat shield; 16. a first cooling hole; 17. a second cooling hole.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An afterburner chamber with air-cooled tandem struts for rectification, as shown in fig. 1-3, includes a rectification system, an ignition combustion system, and a vibration isolation system. The rectification system is used for rectifying the contained airflow, the ignition combustion system is used for ignition and combustion of the heating combustion chamber, and the anti-vibration system is used for inhibiting oscillation combustion of the afterburner.
The rectification support plate comprises a front support plate 2, a rear support plate 1, an inner cone 3 and a converging ring 5, wherein the inner cone 3 and the converging ring 5 are coaxially arranged, and the axial directions of the inner cone 3 and the converging ring 5 are the axial directions of the aero-engine. An inner culvert channel is formed between the inner cone 3 and the converging ring 5 and used for circulating inner culvert air flow, and an outer culvert cooling channel is arranged on the outer side of the converging ring 5 and used for circulating outer culvert cooling air.
Preceding extension board 2 and backplate 1 set up along the even interval of circumference direction of inner cone 3, preceding extension board 2 and backplate 1 paste mutually and preceding extension board 2's trailing edge and the crisscross setting of backplate 1's leading edge, back extension board 1 includes turn-round section 9 and straight section 10, turn-round section 9's turn-round degree is less than preceding extension board 2's turn-round degree, the chamfer has been seted up to preceding extension board 2's trailing edge department, and the chamfer is 45 for the axis direction that inclines in aeroengine, guarantees the rectification effect after the rectification of inner culvert air current is accomplished in preceding extension board 2 department through setting up the chamfer.
When carrying out afterburning, the connotative air current is earlier between two adjacent preceding extension boards 2, and preceding extension board 2 has great degree of turning round, can carry out the rectification of great angle to the connotative air current, and its angle of flow reduces by a wide margin after the rectification is accomplished in extension board 2 in the front, then enters into and carries out rectification once more in the turn round section 9 of back extension board 1, and the connotative air current flows along straight section 10 after the rectification is accomplished, organizes the burning. Preceding extension board 2 and back extension board 1 accomplish the rectification of containing air current under the big import air current angle through twice rectification, compare in current single extension board, the shared whole cross-section space of front extension board 2 and back extension board 1 does not increase by much, and the flow area of containing air current in rectification extension board department does not take place too big change, and the required whole length of while rectification reduces, and weight reduction, afterburner's length reduction, afterburner weight reduces by a wide margin. The number of the flow rectification components is determined by the width of the tail edge of the rear supporting plate 1, the diameter of the afterburner and the acceptable blockage ratio of the afterburner.
Preferably, a first rectifying channel 11 is formed between adjacent front support plates 2, a second rectifying channel 12 communicated with the first rectifying channel 11 is formed between adjacent bent and twisted sections 9, a group combustion channel 13 communicated with the second rectifying channel 12 is formed between adjacent straight sections 10, and the length of the group combustion channel 13 is greater than that of the second rectifying channel 12. Through setting up longer group and firing passageway 13, can effectual reduction air loss, guarantee to organize the burning performance.
Preferably, the front edge of the front support plate 2 passes through the middle of the rear support plate 1 along the extension line of the axial direction of the aircraft engine, so that the turbine part is completely shielded, the rear-view visible part is few, and the radar stealth of the afterburner is realized.
Preferably, inner groovy 8 has been seted up to the position department that inner cone 3 corresponds preceding extension board 2 trailing edge, along with shortening of inner cone 3 diameter, the space between preceding extension board 2 and the back board 1 is crescent along the air current flow direction, realizes the diffusion speed reduction, extension board 2 trailing edge diffusion effect is less relatively in the front, and has realized that the in-process that the culvert air current flows in preceding extension board 2 and back board 1 through inner groovy 8 realizes the equipressure gradient molding, reduces the air current reposition of redundant personnel, reduces the air current diffusion loss.
Preferably, the ignition combustion system comprises an oil spray rod 7, the oil spray rod 7 is arranged inside the rear support plate 1, and an oil spray hole corresponding to the oil spray rod 7 is formed in the rear edge of the rear support plate 1. Insert oil spout pole 7 to the extension board, the air current that can not include flows and causes the hindrance, reduces the air current loss, and the fuel on the oil spout pole 7 passes through the nozzle opening blowout, does not set up the stabilizer structure simultaneously, has effectively reduced afterburner's length and weight, and the rest of ignition combustion system is current design, specifically no longer gives details.
Preferably, the anti-vibration system comprises a diffuser outer wall 4 and an anti-vibration heat shield 6, a bypass cooling channel is formed between the diffuser outer wall 4 and the anti-vibration heat shield 6, a cooling hole communicated with the bypass cooling channel is formed in the anti-vibration heat shield 6, and the bypass cooling channel and a third cooling hole of the anti-vibration heat shield 6 form a helmholtz resonator.
The outer side of converging ring 5 is located to the diffuser outer wall 4 is coaxial, antivibration heat shield 6 includes horizontal heat shield 14 and wave heat shield 15 that coaxial continuous, horizontal heat shield 14's length direction sets up along aircraft engine's axis direction, wave heat shield 15's cross section is the wave, horizontal heat shield 14 and backplate 1 have the interval between.
Horizontal heat screen 14 plays the function of restraining the vibration burning to outer culvert cooling gas and connotative gas, and outer culvert cooling gas is better at 15 gas film adherence of wave heat screen, and hot coordination is better, and the cooperation cooling hole can carry out better cooling to afterburner, and both mutually support, effectively guarantee the stability of burning and the stability that the air current flows.
Preferably, a backflow area is formed among the rear support plate 1, the horizontal heat shield 14 and the inner cone 3, and a backflow area with a larger width can be formed behind the rear support plate 1 by arranging the longer straight section 10, so that the tissue combustion performance is effectively improved.
Preferably, the outer side of the converging ring 5 is provided with a bypass cooling channel, inner cavities communicated with the bypass cooling channel are formed in the front support plate 2 and the rear support plate 1, the side walls of the front support plate 2 and the rear support plate 1 are provided with first cooling holes 16 communicated with the inner cavities, the first cooling holes 16 can be in on-way cooling with the front support plate 2 and the rear support plate 1, the inner part of the inner cone 3 is communicated with the inner cavities, the side wall of the inner cone 3 is provided with second cooling holes 17 communicated with the inner part of the inner cone 3, and the second cooling holes 17 can be used for in-way cooling the inner cone 3.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. An afterburner using air-cooled tandem struts for rectification, comprising a rectification system and an ignition combustion system, characterized in that: the rectification extension board includes preceding extension board (2), back extension board (1), inner cone (3) and confluence ring (5), preceding extension board (2) and back extension board (1) set up along the even interval of the circumferential direction of inner cone (3), preceding extension board (2) and back extension board (1) paste mutually and the trailing edge of preceding extension board (2) sets up with the leading edge of back extension board (1) is crisscross, back extension board (1) is including turn round section (9) and straight section (10), the turn round degree of turn round section (9) is less than the turn round degree of preceding extension board (2), the chamfer angle has been seted up to the trailing edge department of preceding extension board (2).
2. The afterburner with air-cooled tandem strakes as set forth in claim 1, wherein: a first rectifying channel (11) is formed between the adjacent front support plates (2), a second rectifying channel (12) communicated with the first rectifying channel (11) is formed between the adjacent bent and twisted sections (9), a group combustion channel (13) communicated with the second rectifying channel (12) is formed between the adjacent straight sections (10), and the length of the group combustion channel (13) is greater than that of the second rectifying channel (12).
3. The afterburner with air-cooled tandem strip rectification as set forth in claim 1, wherein: the front edge of the front support plate (2) passes through the middle part of the rear support plate (1) along the extension line of the axial direction of the aircraft engine.
4. The afterburner with air-cooled tandem strakes as set forth in claim 1, wherein: an inner groove (8) is formed in the position, corresponding to the tail edge of the front support plate (2), of the inner cone (3).
5. The afterburner with air-cooled tandem strip rectification as set forth in claim 1, wherein: the ignition combustion system comprises an oil spray rod (7), the oil spray rod (7) is arranged inside the rear support plate (1), and an oil spray hole corresponding to the oil spray rod (7) is formed in the rear edge of the rear support plate (1).
6. The afterburner with air-cooled tandem strip rectification as claimed in claim 5, wherein: still include the antivibration system, the antivibration system includes diffuser outer wall (4) and antivibration heat screen (6), the outside of converging ring (5) is located to diffuser outer wall (4) is coaxial, antivibration heat screen (6) are including horizontal heat screen (14) and wave heat screen (15) that coaxial linking to each other, the length direction of horizontal heat screen (14) sets up along aircraft engine's axis direction, the cross section of wave heat screen (15) is the wave, horizontal heat screen (14) and after board (1) between have the interval.
7. The afterburner with air-cooled tandem strakes as set forth in claim 6, wherein: a backflow area is formed among the rear support plate (1), the horizontal heat shield (14) and the inner cone (3).
8. The afterburner with air-cooled tandem strakes as set forth in claim 1, wherein: the outer side of the flow combining ring (5) is provided with a bypass cooling channel, inner cavities communicated with the bypass cooling channel are formed in the front supporting plate (2) and the rear supporting plate (1), first cooling holes (16) communicated with the inner cavities are formed in the side walls of the front supporting plate (2) and the rear supporting plate (1), the inner portion of the inner cone (3) is communicated with the inner cavities, and second cooling holes (17) communicated with the inner portion of the inner cone (3) are formed in the side wall of the inner cone (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210863210.8A CN115200038B (en) | 2022-07-21 | 2022-07-21 | Afterburner adopting air-cooled serial support plates for rectification |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210863210.8A CN115200038B (en) | 2022-07-21 | 2022-07-21 | Afterburner adopting air-cooled serial support plates for rectification |
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| CN115200038A true CN115200038A (en) | 2022-10-18 |
| CN115200038B CN115200038B (en) | 2023-08-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116182197A (en) * | 2022-12-26 | 2023-05-30 | 中国科学院工程热物理研究所 | Ablation-preventing structure for wall surface of afterburner |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116182197A (en) * | 2022-12-26 | 2023-05-30 | 中国科学院工程热物理研究所 | Ablation-preventing structure for wall surface of afterburner |
| CN116182197B (en) * | 2022-12-26 | 2024-05-03 | 中国科学院工程热物理研究所 | Ablation-preventing structure for wall surface of afterburner |
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| CN115200038B (en) | 2023-08-22 |
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