CN113203103A - Pulse detonation combustion chamber head with precombustion chamber structure - Google Patents
Pulse detonation combustion chamber head with precombustion chamber structure Download PDFInfo
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- CN113203103A CN113203103A CN202110491446.9A CN202110491446A CN113203103A CN 113203103 A CN113203103 A CN 113203103A CN 202110491446 A CN202110491446 A CN 202110491446A CN 113203103 A CN113203103 A CN 113203103A
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- precombustion chamber
- detonation
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- 238000005474 detonation Methods 0.000 title claims abstract description 86
- 238000002485 combustion reaction Methods 0.000 title description 12
- 239000000446 fuel Substances 0.000 claims description 29
- 230000003014 reinforcing effect Effects 0.000 claims description 12
- 238000003466 welding Methods 0.000 claims description 5
- 230000004323 axial length Effects 0.000 abstract description 6
- 230000006641 stabilisation Effects 0.000 abstract description 2
- 238000011105 stabilization Methods 0.000 abstract description 2
- 230000000977 initiatory effect Effects 0.000 description 5
- 238000004880 explosion Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000002708 enhancing effect Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing 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
- F23R3/28—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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention discloses a pulse detonation combustor head with a precombustion chamber structure, which comprises a head body, an outer casing, a precombustion chamber and an ignition nozzle mounting seat, wherein the head body is arranged in the outer casing; the precombustion chamber is fixedly mounted on the head body, a plurality of jet holes are respectively formed in two side walls of the precombustion chamber, and the jet holes are staggered in the radial direction. By improving the ignition performance, the working frequency of the detonation chamber is improved, and the working range of the detonation chamber is widened. Ignition and flame stabilization of the detonation chamber are finished in the precombustion chamber, so that mainstream high-speed airflow is avoided, the detonation chamber is not easy to blow out, and the working performance of the detonation chamber is effectively improved; the ignition energy is improved, and the axial length of the detonation chamber is shortened. The whole detonation chamber is ignited by the strong heat emitted by the precombustion chamber, so that detonation can be directly induced, the DDT distance is shortened, and the axial length of the detonation chamber is further shortened.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a pulse detonation combustor head with a pre-combustion chamber structure.
Background
The Pulse Detonation Engine (PDE) is a new concept engine which generates thrust by using high-temperature and high-pressure gas generated by periodic detonation waves, has the advantages of high cycle thermal efficiency, self-pressurization, simple structure and the like, and is widely concerned by domestic and foreign researchers. Detonation initiation technology has been the focus and difficulty of pulse detonation engine research. Detonation of pulse detonation engines generally has two methods; direct initiation and indirect initiation. Direct detonation is the direct detonation triggered by high energy, and the required ignition device is bulky and is impractical in actual operation.
Indirect initiation is usually used at this stage, and the specific way is weak spark or pre-explosion tube ignition. The weak spark ignition means that a flame core is formed by using the traditional spark plug ignition, and then the conversion from slow combustion to detonation (DDT) is realized by a flame acceleration method. The pre-detonation tube ignition means that a pre-detonation tube is arranged above the detonation tube, reactants which are easy to detonate are filled in the pre-detonation tube, and hot air is jetted out to detonate a main detonation chamber after the pre-detonation tube forms detonation.
The initiation mode of the pulse detonation combustor at the present stage is usually weak spark ignition or pre-detonation tube ignition. The weak spark ignition form, although simple, requires a longer DDT process due to the small ignition energy. Stability can worsen when high detonation frequency work simultaneously, can't form the detonation wave of full development, and the reason has two: 1) along with the increase of the detonation frequency, the incoming flow speed is correspondingly increased, the mixed explosive mixture is difficult to enter the ignition vortex hole, and the explosive mixture in the ignition vortex hole is low in concentration and difficult to ignite reliably; 2) even if the ignition in the ignition vortex hole is successful, the generated weak flame is difficult to smoothly spread and accelerate due to the overhigh flow velocity of the mixture in the main detonation chamber, and the quenching is easy to occur. The ignition of the pre-explosion tube needs to additionally carry highly sensitive fuel and oxidant, and meanwhile, the pre-explosion tube needs to be matched with the main explosion tube, so that the difficulty of a control system is increased.
Disclosure of Invention
Aiming at the defects of the existing ignition and detonation technology of the pulse detonation combustor, the invention provides a pulse detonation combustor head with a pre-combustion chamber structure, which can effectively improve the ignition performance and increase the ignition energy entering a detonation section, thereby shortening the axial length of the detonation chamber, improving the detonation frequency and effectively improving the working performance of the pulse detonation combustor.
The purpose of the invention can be realized by the following technical scheme:
a pulse detonation combustor head with a precombustion chamber structure comprises a head body, an outer casing, a precombustion chamber and an ignition nozzle mounting seat, wherein the head body is arranged in the outer casing, the rear end of the outer casing is fixedly connected with the head body in a welding mode, and the outer casing and the head body form two channels; the precombustion chamber fixed mounting be in on the head body, a plurality of jet orifice has been seted up respectively to precombustion chamber both sides wall, the jet orifice radially staggers for make the high-pressure air that gets into form the recirculation zone in the precombustion chamber, wall fixed mounting has first fuel nozzle before the precombustion chamber, precombustion chamber top fixed mounting has the ignition nozzle.
Further: two rows of radially staggered jet holes are formed in the side wall of the precombustion chamber, each row of jet holes is seven, and seven jet holes are circumferentially and equidistantly distributed.
Further: a first mounting hole is formed in the wall surface of the precombustion chamber, and a first mounting seat used for fixedly mounting a first fuel nozzle is sleeved on the first mounting hole.
Further: and a second mounting hole is formed in the top of the precombustion chamber, and a second mounting seat for fixedly mounting an ignition electric nozzle is sleeved on the second mounting hole.
Further: the distance between the first fuel nozzle and the head body is larger than the distance between the two rows of jet holes and the head body.
Further: and a second fuel nozzle is arranged on the side wall of the head body close to the high-pressure air inlet end.
Further: and a third mounting hole is formed in the position, corresponding to the second fuel nozzle, of the head body, and a third mounting seat for fixedly mounting the second fuel nozzle is sleeved on the third mounting hole.
Further: the centers of the first fuel nozzle, the ignition nozzle and the second fuel nozzle are on the same plane.
Further: the precombustion chamber is of a cuboid structure.
Further: one end of the head body extends out of the outer casing and is fixedly welded with a flange mounting edge, one side, away from the head body, of the flange mounting edge is provided with a detonation reinforcing section, and the detonation reinforcing section is fixedly connected with the flange mounting edge through a bolt.
Further: and a spring-shaped detonation reinforcing device is tightly welded and fixed on the inner wall of the detonation reinforcing section.
The invention has the beneficial effects that:
1. by improving the ignition performance, the working frequency of the detonation chamber is improved, and the working range of the detonation chamber is widened. The head body is provided with a precombustion chamber, fuel and air flow into the precombustion chamber in a specific mode, and a backflow area is formed by upper and lower rows of staggered jet holes. Ignition and flame stabilization of the detonation chamber are both completed in the pre-combustion chamber, so that mainstream high-speed airflow is avoided, the detonation chamber is not easy to blow out, the ignition performance is superior, the working performance of the detonation chamber is effectively improved, after flame of the pre-combustion chamber is fully developed, high-temperature hot jet flow is formed and enters a main flow area, combustible mixed gas in the main flow area is ignited to form hot jet flow with higher energy, compared with the traditional method that a flame core is formed by ignition of a spark plug, and then the transition from slow combustion to detonation is realized through flame acceleration, the detonation forming time is greatly shortened due to the arrangement of the pre-combustion chamber, the pulse detonation wave frequency is improved, and more work is done in unit time by an engine adopting the head of the pulse detonation combustion chamber;
2. the ignition energy is improved, and the axial length of the detonation chamber is shortened. The whole detonation chamber is ignited by the strong heat emitted by the precombustion chamber, so that detonation can be directly induced, the DDT distance is shortened, and the axial length of the detonation chamber is further shortened.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic view of a pulse detonation combustor head with a pre-combustion chamber configuration;
FIG. 2 is a schematic view of the overall structure of the present invention;
fig. 3 is a schematic structural diagram of the mounting base of the present invention.
In the figure: 1. a head body; 2. an outer case; 3. a precombustion chamber; 31. a jet hole; 4. a second mounting seat;
5. a first mounting seat; 6. a third mounting seat; 7. an ignition electric nozzle; 8. a first fuel injection nozzle; 9. a second fuel nozzle; 10. a bolt; 11. a detonation-enhancing section; 12. a knock intensifying device; 101. and (5) mounting the flange.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 3, a preferred embodiment of the present invention provides a pulse detonation combustor head with a precombustion chamber structure, which includes a head body 1, an outer casing 2, a precombustion chamber 3 and an ignition electric nozzle 7 mounting base, wherein the outer casing 2 is internally provided with the head body 1, the rear end of the outer casing 2 is fixedly connected with the head body 1 in a welding manner, and the outer casing and the head body 1 form two channels; the precombustion chamber 3 is fixedly arranged on the head body 1, a plurality of jet holes 31 are respectively formed in two side walls of the precombustion chamber 3, the jet holes 31 are staggered in the radial direction and used for enabling the entering high-pressure air to form a backflow zone in the precombustion chamber 3, a first fuel nozzle 8 is fixedly arranged on the front wall surface of the precombustion chamber 3, and an ignition electric nozzle 7 is fixedly arranged at the top of the precombustion chamber 3; two rows of radially staggered jet holes 31 are formed in the side wall of the precombustion chamber 3, seven jet holes 31 are formed in each row of jet holes 31, and seven jet holes 31 are circumferentially and equidistantly distributed; a first mounting hole is formed in the front wall of the precombustion chamber 3, and a first mounting seat 5 for fixedly mounting a first fuel nozzle 8 is sleeved on the first mounting hole; a second mounting hole is formed in the top of the precombustion chamber 3, and a second mounting seat 4 for fixedly mounting an ignition electric nozzle 7 is sleeved on the second mounting hole; the distance of the first fuel nozzle 8 relative to the head body 1 is greater than the distance of the two rows of jet holes 31 relative to the head body 1; a second fuel nozzle 9 is arranged on the side wall of the head body 1 close to the high-pressure air inlet end; a third mounting hole is formed in the position, corresponding to the second fuel nozzle 9, of the head body 1, and a third mounting seat 6 for fixedly mounting the second fuel nozzle 9 is sleeved on the third mounting hole; the precombustion chamber 3 is of a cuboid structure; one end of the head body 1 extends out of the outer casing 2 and is fixedly welded with a flange mounting edge 101, one side, away from the head body 1, of the flange mounting edge 101 is provided with a detonation reinforcing section 11, and the detonation reinforcing section 11 is fixedly connected with the flange mounting edge 101 through a bolt 10; the inner wall of the detonation reinforcing section 11 is tightly welded and fixed with a spring-shaped detonation reinforcing device 12.
In the present embodiment, the prechamber 3, the outer casing 2, and the third mount base 6 are preferably fixed to the head body 1 by welding, and the first mount base 5 and the second mount base 4 are preferably fixed to the prechamber 3 by welding. The head body 1 is a metal cylinder with a flange at the rear end and a third mounting seat 6, the inner diameter is 60mm, the wall thickness is 3mm, and the length is 170 mm. The outer casing 2 is a front section with a flange, the inner diameter of the air inlet section is 40mm, the wall thickness is 2mm, and the expansion angle is 45 degrees. The precombustion chamber 3 is a cuboid structure, and has the axial length of 30mm, the radial height of 43mm and the axial width of 40 mm. The upper and lower rows of staggered jet holes 31 are distributed along the radial direction, each row is 7, the radial height is 53.5mm and 45mm respectively, and the aperture is 3 mm.
The ignition device and the knock enhancing device are connected by bolts 10 as shown in fig. 2. In a pulse detonation period, firstly high-pressure air enters the head of a detonation chamber, part of gas enters the head body 1 and is mixed with fuel oil injected by a second fuel nozzle 9 to form combustible mixed gas, and the combustible mixed gas continuously flows into a main combustion area; the other part of the gas enters into two channels formed by the head body 1 and the outer casing 2, enters into the precombustion chamber 3 through the jet holes 31 of the precombustion chamber 3, and forms a backflow area under the action of the upper row and the lower row of jet flows. A first fuel nozzle 8 arranged on the front wall surface of the precombustion chamber 3 injects fuel to form combustible mixture, and an ignition electric nozzle 7 at the top ignites. After the flame of the precombustion chamber 3 is fully developed, high-temperature heat jet flow is formed and enters the main flow area, combustible mixed gas in the main flow area is ignited to form heat jet flow with larger energy, the heat jet flow is gradually enhanced under the action of the detonation enhancing device 12 in the detonation enhancing section 11, and finally stable high-frequency detonation is formed.
The foregoing is merely exemplary and illustrative of the present invention and various modifications, additions and substitutions may be made by those skilled in the art to the specific embodiments described without departing from the scope of the invention as defined in the following claims.
Claims (11)
1. A pulse detonation combustor head with a precombustion chamber structure comprises a head body, an outer casing, a precombustion chamber and an ignition nozzle mounting seat, and is characterized in that the head body is arranged in the outer casing, the rear end of the outer casing is fixedly connected with the head body in a welding mode, and the outer casing and the head body form two channels; the precombustion chamber fixed mounting be in on the head body, a plurality of jet orifice has been seted up respectively to precombustion chamber both sides wall, the jet orifice radially staggers for make the high-pressure air that gets into form the recirculation zone in the precombustion chamber, wall fixed mounting has first fuel nozzle before the precombustion chamber, precombustion chamber top fixed mounting has the ignition nozzle.
2. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 1, wherein the precombustion chamber has two rows of radially staggered jet holes, and each row of jet holes has seven jet holes, and the seven jet holes are circumferentially equidistantly distributed.
3. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 1, wherein the wall surface of the precombustion chamber is provided with a first mounting hole, and a first mounting seat for fixedly mounting a first fuel nozzle is sleeved on the first mounting hole.
4. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 1, wherein a second mounting hole is formed in the top of the precombustion chamber, and a second mounting seat for fixedly mounting an ignition burner is sleeved on the second mounting hole.
5. The pulse detonation combustor head with a prechamber structure of claim 1, characterized in that the distance of the first fuel nozzle relative to the head body is greater than the distance of two rows of jet holes relative to the head body.
6. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 1, wherein a second fuel nozzle is disposed on a side wall of the head body near a high-pressure air intake end.
7. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 6, wherein a third mounting hole is formed in a position of the head body corresponding to the second fuel nozzle, and a third mounting seat for fixedly mounting the second fuel nozzle is sleeved on the third mounting hole.
8. The pulse detonation combustor head with a precombustion chamber structure of claim 1, wherein centers of the three components of the first fuel nozzle, the ignition burner and the second fuel nozzle are on the same plane.
9. The pulse detonation combustor head with a prechamber structure of claim 1, wherein the prechamber is a rectangular parallelepiped structure.
10. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 1, wherein one end of the head body extends out of the outer casing and is fixedly welded with a flange mounting edge, a detonation reinforcing section is arranged on one side of the flange mounting edge, which is away from the head body, and the detonation reinforcing section is fixedly connected with the flange mounting edge through bolts.
11. The pulse detonation combustor head with the precombustion chamber structure as claimed in claim 1, wherein a spring-shaped detonation reinforcing device is tightly welded and fixed on the inner wall of the detonation reinforcing section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110491446.9A CN113203103B (en) | 2021-05-06 | 2021-05-06 | Pulse detonation combustion chamber head with precombustion chamber structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110491446.9A CN113203103B (en) | 2021-05-06 | 2021-05-06 | Pulse detonation combustion chamber head with precombustion chamber structure |
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| CN113203103A true CN113203103A (en) | 2021-08-03 |
| CN113203103B CN113203103B (en) | 2022-03-29 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001375A (en) * | 2021-11-12 | 2022-02-01 | 西安热工研究院有限公司 | A rotary detonation combustion chamber with a pre-combustion chamber |
| CN118997950A (en) * | 2024-08-13 | 2024-11-22 | 中国人民解放军军事航天部队航天工程大学 | Rotary detonation rocket engine with staged combustion |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001375A (en) * | 2021-11-12 | 2022-02-01 | 西安热工研究院有限公司 | A rotary detonation combustion chamber with a pre-combustion chamber |
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| CN118997950A (en) * | 2024-08-13 | 2024-11-22 | 中国人民解放军军事航天部队航天工程大学 | Rotary detonation rocket engine with staged combustion |
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| CN113203103B (en) | 2022-03-29 |
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