CN115628464A - Three-channel scramjet engine combustion chamber - Google Patents
Three-channel scramjet engine combustion chamber Download PDFInfo
- Publication number
- CN115628464A CN115628464A CN202211249496.7A CN202211249496A CN115628464A CN 115628464 A CN115628464 A CN 115628464A CN 202211249496 A CN202211249496 A CN 202211249496A CN 115628464 A CN115628464 A CN 115628464A
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- section
- combustion chamber
- short slab
- straight section
- stable combustion
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 88
- 239000000446 fuel Substances 0.000 claims abstract description 34
- 238000002347 injection Methods 0.000 claims abstract description 21
- 239000007924 injection Substances 0.000 claims abstract description 21
- 238000005192 partition Methods 0.000 claims abstract description 18
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 17
- 238000002955 isolation Methods 0.000 claims abstract description 17
- 239000001301 oxygen Substances 0.000 claims abstract description 17
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 17
- 239000007921 spray Substances 0.000 claims description 7
- 230000000087 stabilizing effect Effects 0.000 description 12
- 230000000694 effects Effects 0.000 description 6
- 238000002474 experimental method Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000001965 increasing effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 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
- F23R3/02—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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention discloses a three-channel scramjet engine combustion chamber, and particularly relates to the field of scramjets. The combustion chamber consists of an isolation section, an expansion section and an equal straight section, the isolation section, the expansion section and the equal straight section are connected through flanges, two partition plates are distributed in the combustion chamber, and first fuel injection holes respectively positioned in the isolation section, the expansion section and the equal straight section are formed in two sides of each partition plate; three stable combustion support plates are arranged in the combustion chamber, the three stable combustion support plates are respectively arranged between the two partition plates and the combustion chamber and between the two partition plates, a second fuel injection hole and an oxygen supply hole are formed in each stable combustion support plate, the second fuel injection hole is formed in the front of each stable combustion support plate, the oxygen supply hole is formed in the side face of each stable combustion support plate, a groove located outside the oxygen supply hole is further formed in the side face of each stable combustion support plate, and a plasma igniter is arranged in each groove. By adopting the technical scheme of the invention, the problem of thrust lifting of the combustion chamber is solved, and the integral thrust of the combustion chamber can be improved.
Description
Technical Field
The invention relates to the field of scramjet engines, in particular to a three-channel scramjet engine combustion chamber.
Background
The scramjet engine has been widely discussed by many scholars at home and abroad because of its high specific impulse, high speed and safety which are much higher than those of rockets. The supersonic combustor is one of the important components of the scramjet engine, and the essential work of the supersonic combustor is to provide stable and high-amount effective thrust for an aircraft.
To achieve this goal, combustors with severely limited structure and mass inevitably place demands on the flame stabilizer. The currently adopted stable combustion mode mainly comprises support plate stable combustion and concave cavity stable combustion, in the extensive research process, the support plate stable combustion gradually derives a support plate/wall stable combustion mode, the multi-stage heat release capability of the combustion chamber is greatly enhanced, the stable working time of the combustion chamber is prolonged, but a bottleneck stage is reached in the long-time development process. Under the limitation of the energy equation, in order to further increase the thrust of the combustion chamber, a higher intensity heat release rate inside the combustion chamber is required. It has been proposed by the scholars to increase the fuel consumption in the same time by increasing the intake air flow, so as to break the heat dissipation barrier and obtain higher thrust, but in the field of gas dynamics, the choking effect of the duct, the combustion chamber inlet flow can only approach the limit value and cannot be exceeded. Therefore, the geometric structure of the combustion chamber needs to be changed, but the geometric similarity is limited by a scale effect, and the geometric similarity is only carried out through simple area expansion, so that the related dynamic similarity conditions cannot be simultaneously met, for example, the effective thrust of the combustion chamber is reduced due to extra loss such as thickening of a boundary layer of the combustion chamber, and the performance of the combustion chamber is improved and tends to be flat and thin.
Disclosure of Invention
The invention aims to provide a three-channel scramjet engine combustion chamber, and solves the problem of thrust lifting of the combustion chamber.
In order to achieve the purpose, the technical scheme of the invention is as follows: a three-channel scramjet engine combustion chamber is composed of an isolation section, an expansion section and an equal straight section, wherein the isolation section, the expansion section and the equal straight section are connected with each other through flanges; the plasma ignition device is characterized in that three stable combustion support plates are arranged in the combustion chamber, the three stable combustion support plates are respectively arranged between the two partition plates and the inner wall of the combustion chamber and between the two partition plates, a second fuel injection hole and an oxygen supply hole are formed in each stable combustion support plate, the second fuel injection holes are formed in the front of each stable combustion support plate, the oxygen supply holes are formed in the side faces of the stable combustion support plates, grooves located outside the oxygen supply holes are further formed in the side faces of the stable combustion support plates, and plasma igniters are installed in the grooves.
Further, the baffle comprises the first short slab of polylith, the short slab of second and the short slab of third, first short slab sets up in the isolated section, the both ends of the short slab of second stretch into isolated section and equal straight section respectively, the short slab of third sets up in equal straight section, the recess that has mutual lock joint is all opened in the department of meeting of first short slab and the short slab of second, the short slab of second and the short slab of third.
Through the arrangement, the grooves are used for fastening, so that replaceability and experiment variability can be increased on the premise of ensuring stable work of the combustion chamber.
Compared with the prior art, the beneficial effect of this scheme:
the scheme provides a three-channel scramjet engine combustion chamber for further enhancing the pressure rise performance of a supersonic combustion chamber and improving the effective thrust of a scramjet engine based on a support plate/wall surface oil injection stable combustion strategy. The large-scale combustion chamber is divided into three channels which are connected in parallel and work independently through the partition plate, on one hand, the three channels are equivalent to the three combustion chambers which work in parallel, and the stable combustion capacity is exerted through the stable combustion support plates respectively; on the other hand, the potential problems brought by the scale effect are reduced while the air inflow is improved, and the effective thrust of the combustion chamber is further improved by utilizing the wall surface oil spray holes of the partition plates to realize multi-stage heat release in each channel; meanwhile, the method starts from two aspects of providing large air inlet flow and avoiding scale effect generated by geometric similarity, improves the fuel consumption and heat release of the supersonic combustion chamber to generate high pressure rise, and further improves the overall thrust of the scramjet.
Drawings
FIG. 1 is a top view of a three-channel scramjet combustion chamber of the present invention;
FIG. 2 is a front view of a three-channel scramjet combustion chamber of the present invention;
FIG. 3 isbase:Sub>A cross-sectional view A-A of FIG. 2;
FIG. 4 is a cross-sectional view B-B of FIG. 3;
FIG. 5 is a top view of the combustion stabilizing support plate in the present embodiment;
fig. 6 is a rear view of the flame stabilizing plate in the present embodiment.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the fuel injection device comprises an isolation section 1, an expansion section 2, an equal straight section 3, a partition plate 4, a first fuel injection hole 5, a combustion stabilizing support plate 6, a second fuel injection hole 7, an oxygen supply hole 8, a groove 9, an annular fuel injector 10 and a third fuel injection hole 11.
Examples
As shown in the attached drawings 1-6, the three-channel scramjet engine combustion chamber is composed of an isolation section 1, an expansion section 2 and an equal straight section 3, the isolation section 1, the expansion section 2 and the equal straight section 3 are connected with each other through flanges, an annular fuel injector 10 is abutted between two flanges of the expansion section 2 and the equal straight section 3, the annular fuel injector 10 is composed of a rectangular frame structure and a plurality of third fuel spray holes 11 which are distributed on four side walls in the frame structure at equal intervals, and the third fuel spray holes 11 are respectively positioned in each channel. The isolation section 1 is used for resisting the non-starting phenomenon induced by back pressure generated by combustion in a combustion chamber and ensuring the stable work of a front air inlet; the expansion section 2 is used for providing high-pressure low-distortion air for an internal flow field and increasing the heat release space improvement performance of the combustion chamber; the equal straight section 3 can generate a thermal throat in a sub-combustion mode to accelerate the sub-sonic airflow to a supersonic speed state.
There are two baffles 4 at interval equidistance distribution in the combustion chamber, every baffle 4 all extends to equal straight section 3 from keeping apart section 1, baffle 4 inlays to be established in keeping apart section 1, expand section 2 and equal straight section 3 in, baffle 4 is by the first short slab of polylith, second short slab and third short slab are constituteed, first short slab sets up at keeping apart section 1, the both ends of second short slab stretch into respectively keeps apart section 1 and equal straight section 3, the third short slab sets up at equal straight section 3, first short slab and second short slab, the department of meeting of second short slab and third short slab all opens the recess 9 of mutual lock joint, utilize recess 9 to carry out the lock joint can increase the polytropy of changeability and experiment under the prerequisite of guaranteeing the stable work of combustion chamber. The two sides of the baffle plate 4 are respectively provided with a first fuel injection hole 5 which is respectively positioned in the isolation section 1, the expansion section 2 and the equal straight section 3. The first fuel injection holes 5 have a diameter of 0.5mm, are 6 in number and are longitudinally and uniformly distributed on the partition plate 4, thereby realizing multi-stage injection of fuel.
The two baffles 4 and the inner wall of the combustion chamber and the two baffles 4 form gas inlet and outlet channels, a combustion stabilizing support plate 6 with the thickness of 6mm is arranged in each channel, a through hole which is connected with the combustion stabilizing support plate 6 in a sliding and sealing manner is formed in the expansion section 2, each combustion stabilizing support plate 6 is arranged in the center of each channel, the tail part of each combustion stabilizing support plate 6 and the cross section expansion part of the expansion section 2 are positioned in the same plane, second fuel injection holes 7 which are symmetrically distributed on the combustion stabilizing support plate 6 and two rows of oxygen supply holes 8 which are arranged at intervals are formed in the combustion stabilizing support plate 6, the second fuel injection holes 7 are arranged on the front surface of the combustion stabilizing support plate 6 and are mutually vertical to incoming flow, the two rows of oxygen supply holes 8 are arranged on the side surface and are parallel to the incoming flow, grooves 9 which are positioned in front of the two rows of oxygen supply holes 8 are further formed in the side surface of the combustion stabilizing support plate 6, and plasma igniters are arranged in the grooves 9. The fuel injection holes realize momentum exchange between the fuel and high-speed airflow in the flowing process along the side wall of the support plate through countercurrent injection, so that the mixing efficiency is improved; the oxygen supply hole 8 supplies oxygen and forms a low-speed reflux zone and a free shear layer at the tail edge of the support plate to further enhance mixing; and a plasma igniter is arranged at the position of the groove 9, and the gas-liquid two-phase fuel gathered at the position is ignited by high energy injected by the igniter to form initial flame.
The working process of the scheme is as follows:
supersonic airflow is divided by a partition plate 4 at the inlet of a combustion chamber and enters three independently working isolation sections 1, fuel is injected into the combustion chamber through a stable combustion support plate 6 at the outlet section, and initial stable flame is established under the working of an igniter. In the scheme, a low-speed backflow area is established at the tail part of the combustion stabilizing support plate 6 by using oxygen injected from the oxygen supply hole 8, and meanwhile, fuel injected from the second fuel injection hole 7 positioned at the upstream is ignited by a plasma igniter in a shearing layer to form stable flame. The oil spray holes uniformly arranged on the partition plate 4 are matched with the integrally processed wall surface oil spray ring to realize the multi-stage injection and combustion organization of the fuel. Because the design purpose is mainly to do the experiment, for the design demand that realizes that experiment is convenient for change and repeated experiment many times, baffle 4 adopts dock mechanical fastening, has possessed the function of partition channel and wall oil spout simultaneously, has promoted convertibility and subsequent experiment variability under the prerequisite that satisfies stability. In the three-channel combustion chamber, supersonic airflow enters different channels through shunting at the inlet of the combustion chamber to establish stable combustion, so that potential problems caused by the scale effect of the combustion chamber can be effectively avoided, and stable large thrust is output outwards.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (2)
1. A three-channel scramjet engine combustion chamber is characterized in that: the combustor comprises an isolation section (1), an expansion section (2) and an equal straight section (3), wherein the isolation section (1), the expansion section (2) and the equal straight section (3) are connected through flanges, an annular fuel injector (10) is arranged between two flanges on the expansion section (2) and the equal straight section (3), a plurality of third fuel spray holes (11) are equidistantly formed in four side walls in the annular fuel injector (10), two partition plates (4) are distributed in the combustor at intervals and equidistantly, each partition plate (4) extends from the isolation section (1) to the equal straight section (3), and first fuel spray holes (5) respectively located in the isolation section (1), the expansion section (2) and the equal straight section (3) are formed in two sides of each partition plate (4); the plasma ignition device is characterized in that three stable combustion support plates (6) are arranged in the combustion chamber, the three stable combustion support plates (6) are respectively arranged between the two partition plates (4) and the inner wall of the combustion chamber and between the two partition plates (4), second fuel injection holes (7) and oxygen supply holes (8) are formed in the stable combustion support plates (6), the second fuel injection holes (7) are formed in the front of the stable combustion support plates (6), the oxygen supply holes (8) are formed in the side faces, grooves (9) located outside the oxygen supply holes (8) are further formed in the side faces of the stable combustion support plates (6), and plasma igniters are installed in the grooves (9).
2. The three-channel scramjet engine combustor of claim 1, wherein: baffle (4) comprise the first short slab of polylith, the short slab of second and the short slab of third, first short slab sets up in isolation section (1), the both ends of the short slab of second stretch into isolation section (1) respectively and wait straight section (3), the short slab of third sets up in waiting straight section (3), recess (9) that have mutual lock joint are all opened in the department of meeting of first short slab and the short slab of second, the short slab of second and the short slab of third.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211249496.7A CN115628464A (en) | 2022-10-12 | 2022-10-12 | Three-channel scramjet engine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211249496.7A CN115628464A (en) | 2022-10-12 | 2022-10-12 | Three-channel scramjet engine combustion chamber |
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| Publication Number | Publication Date |
|---|---|
| CN115628464A true CN115628464A (en) | 2023-01-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211249496.7A Pending CN115628464A (en) | 2022-10-12 | 2022-10-12 | Three-channel scramjet engine combustion chamber |
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| Country | Link |
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| CN (1) | CN115628464A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116293802A (en) * | 2023-03-14 | 2023-06-23 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150013305A1 (en) * | 2009-11-19 | 2015-01-15 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | Dual-Mode Combustor |
| CN104964310A (en) * | 2015-06-12 | 2015-10-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Ramjet combustion chamber |
| CN107894010A (en) * | 2017-09-15 | 2018-04-10 | 江西洪都航空工业集团有限责任公司 | A kind of laminated board type scramjet engine combustion chamber |
| CN111828201A (en) * | 2020-07-15 | 2020-10-27 | 中国空气动力研究与发展中心 | Conveniently-disassembled ground test device for scramjet engine |
| CN112231903A (en) * | 2020-10-13 | 2021-01-15 | 西北工业大学 | Multi-objective optimization design scheme of circular super-combustion chamber based on genetic algorithm |
| CN114183280A (en) * | 2021-12-13 | 2022-03-15 | 哈尔滨工业大学 | Method for regulating combustion heat release distribution by plasma |
-
2022
- 2022-10-12 CN CN202211249496.7A patent/CN115628464A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150013305A1 (en) * | 2009-11-19 | 2015-01-15 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | Dual-Mode Combustor |
| CN104964310A (en) * | 2015-06-12 | 2015-10-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Ramjet combustion chamber |
| CN107894010A (en) * | 2017-09-15 | 2018-04-10 | 江西洪都航空工业集团有限责任公司 | A kind of laminated board type scramjet engine combustion chamber |
| CN111828201A (en) * | 2020-07-15 | 2020-10-27 | 中国空气动力研究与发展中心 | Conveniently-disassembled ground test device for scramjet engine |
| CN112231903A (en) * | 2020-10-13 | 2021-01-15 | 西北工业大学 | Multi-objective optimization design scheme of circular super-combustion chamber based on genetic algorithm |
| CN114183280A (en) * | 2021-12-13 | 2022-03-15 | 哈尔滨工业大学 | Method for regulating combustion heat release distribution by plasma |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116293802A (en) * | 2023-03-14 | 2023-06-23 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
| CN116293802B (en) * | 2023-03-14 | 2024-05-14 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
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