CN114877376B - Dual-channel detonation combustion chamber - Google Patents
Dual-channel detonation combustion chamber Download PDFInfo
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- CN114877376B CN114877376B CN202210625688.7A CN202210625688A CN114877376B CN 114877376 B CN114877376 B CN 114877376B CN 202210625688 A CN202210625688 A CN 202210625688A CN 114877376 B CN114877376 B CN 114877376B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 246
- 238000005474 detonation Methods 0.000 title claims abstract description 45
- 239000000446 fuel Substances 0.000 claims abstract description 373
- 238000002347 injection Methods 0.000 claims abstract description 138
- 239000007924 injection Substances 0.000 claims abstract description 138
- 239000007800 oxidant agent Substances 0.000 claims abstract description 100
- 230000001590 oxidative effect Effects 0.000 claims abstract description 98
- 230000009977 dual effect Effects 0.000 claims abstract description 9
- 230000000087 stabilizing effect Effects 0.000 claims description 26
- 238000001816 cooling Methods 0.000 claims description 20
- 230000000694 effects Effects 0.000 abstract description 19
- 238000006243 chemical reaction Methods 0.000 abstract description 4
- 238000005728 strengthening Methods 0.000 abstract 1
- 238000013461 design Methods 0.000 description 29
- 239000007921 spray Substances 0.000 description 22
- 238000002156 mixing Methods 0.000 description 19
- 239000000463 material Substances 0.000 description 12
- 238000011160 research Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 10
- 238000003754 machining Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 6
- 238000000889 atomisation Methods 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000002035 prolonged effect Effects 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 238000001125 extrusion Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000003908 quality control method Methods 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- F23R3/42—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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention provides a dual channel detonation combustor, comprising: the combustion chamber inner ring group, the fuel cavity shell and the combustion chamber shell are coaxially sleeved in sequence from inside to outside; the oxidant injection cavity, combustion chamber circular seam shape chamber, first external fuel pipe inner fuel cavity anterior segment, outer fuel cavity anterior segment and second external fuel pipe, the oxidant injection cavity is the annular cavity that forms around fuel cavity shell and the combustion chamber shell, the entrance point in combustion chamber circular seam shape chamber and the exit point in oxidant injection cavity communicate each other, the inner fuel cavity anterior segment is the annular cavity that forms around fuel cavity shell and the combustion chamber inner ring combination, first external fuel pipe sets up at the outer wall of fuel cavity shell and link up with the fuel cavity anterior segment, outer fuel cavity anterior segment sets up radially outside at the oxidant injection cavity, second external fuel pipe communicates with outer fuel cavity anterior segment and inner fuel cavity anterior segment all communicates with combustion chamber circular seam shape chamber. The effect of maintaining stable supply pressure and strengthening thrust conversion can be achieved.
Description
Technical Field
The specification relates to the technical field of aircraft combustors, and in particular relates to a dual-channel detonation combustor.
Background
The aerospace field is more and more competitive, and the research on key innovation technology in the aerospace field is more and more important in various countries. In recent years, with the continuous and intensive research on hypersonic aircrafts and single-stage in-orbit power systems, novel continuous rotary detonation engine technology has been rapidly developed. Research shows that the propulsion technology based on detonation combustion can greatly reduce fuel consumption, greatly improve the specific impulse characteristic of the power device, and has important significance for widening the work envelope of the air suction type aircraft and improving the economical efficiency and operational performance of the existing weaponry. As a leading technology capable of overtaking at a curve, comprehensive and deep researches on the technology are more urgent.
The continuous rotation detonation engine is a power technology utilizing detonation combustion, and is summarized in that: (1) The detonation wave can be continuously transmitted along the circumferential direction of the combustion chamber only by one-time successful detonation; (2) The combustion speed is high, the heat release intensity is high, the combustion chamber has a compact structure, and the length of the engine can be shortened; (3) The device has supercharging property, can reduce the number of compressor stages of a turbine engine or reduce the total pressure loss of an inlet channel of a ramjet engine, is beneficial to simplifying the design of a propulsion system and improving the thrust-weight ratio of the engine; (4) The device can work in an air suction mode or a rocket mode, and the working range can be changed from subsonic speed to supersonic speed with high Mach number. Therefore, research into continuously rotating knock engines has been attracting considerable attention in the scientific community.
The current research on the continuous rotary detonation engine has achieved more results and accumulated more experience, but problems of combustion controllability, fuel blending, injection form, jet hole size or quantity (related to flow control, atomization and mixing), combustion chamber circumferential gap space size, shortest length required by combustion chamber blending, the effect of various injection forms on combustion chamber blending to form combustible mixture ignition to form deflagration to be gradually converted into detonation, combustion chamber regenerative cooling and insufficient thorough research on novel applicable materials are gradually exposed, barriers on engineering roads are more prominent, and the key problems are more key to the end application of the engine. Research on the minimum cross section, the shortest length and the minimum volume of the detonation combustion chamber has also started the pushing of the tightening and tightening drum, and research on the reduction of the inner ring body is a simple and feasible thought. However, the inner ring body is reduced, the flow is correspondingly reduced, and the fuel multi-channel injection is one of the directions of research.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide a dual-channel detonation combustor to achieve the goals of maintaining stable supply pressure and enhancing thrust conversion.
The embodiment of the specification provides the following technical scheme:
a dual channel detonation combustor, comprising:
the combustion chamber shell assembly comprises a combustion chamber inner ring group, a fuel cavity shell and a combustion chamber shell which are coaxial and are sequentially sleeved from inside to outside;
The combustion chamber assembly comprises an oxidant injection cavity, a combustion chamber annular slit-shaped cavity, a first external fuel pipe, an inner fuel cavity front section, an outer fuel cavity front section and a second external fuel pipe, wherein the oxidant injection cavity is an annular cavity formed by encircling a fuel cavity shell and a combustion chamber shell, an inlet end of the combustion chamber annular slit-shaped cavity is communicated with an outlet end of the oxidant injection cavity, the inner fuel cavity front section is an annular cavity formed by encircling a fuel cavity shell and a combustion chamber inner annular, the first external fuel pipe is arranged on the outer wall of the fuel cavity shell and communicated with the front section of the fuel cavity, the outer fuel cavity front section is arranged outside the oxidant injection cavity in the radial direction, the second external fuel pipe is communicated with the front section of the outer fuel cavity, and the front section of the outer fuel cavity is communicated with the annular slit-shaped cavity of the combustion chamber.
Further, the combustion chamber inner ring group comprises an inner ring body and a combustion chamber inner ring, the combustion chamber inner ring is coaxially sleeved outside the inner ring body, the combustion chamber outer shell comprises a combustion chamber first shell and a combustion chamber second shell, the combustion chamber second shell is coaxially sleeved outside the combustion chamber first shell, the fuel cavity outer shell comprises an inner fuel cavity outer shell and an outer fuel cavity inner shell, and the outer fuel cavity inner shell is coaxially sleeved outside the inner fuel cavity outer shell.
Further, the outer fuel cavity front section is an annular cavity formed by encircling a first combustion chamber shell and a second combustion chamber shell, the second external fuel pipe is arranged on the outer wall of the second combustion chamber shell, the inner fuel cavity front section is an annular cavity formed by encircling an inner fuel cavity shell and an inner ring body, and the first external fuel pipe is arranged on the outer wall of the inner fuel cavity shell.
Further, the combustion chamber assembly further comprises an inner ring fuel injection channel, wherein the inner ring fuel injection channel is an axial gap between the inner fuel cavity shell and the inner ring of the combustion chamber, the inlet end of the inner ring fuel injection channel is connected with the front section of the inner fuel cavity, the outlet end of the inner ring fuel injection channel is connected with the annular slit-shaped cavity of the combustion chamber, and the included angle between the inner ring fuel injection channel and the inner wall of the annular slit-shaped cavity of the combustion chamber is theta, and the theta is 30-90 degrees.
Further, the combustion chamber assembly further comprises an outer ring fuel injection channel, wherein the outer ring fuel injection channel is an axial gap between the inner shell of the outer fuel cavity and the first shell of the combustion chamber, the inlet end of the outer ring fuel injection channel is connected with the front section of the outer fuel cavity, the outlet end of the outer ring fuel injection channel is connected with the annular slot-shaped cavity of the combustion chamber, the included angle between the outer ring fuel injection channel and the inner wall of the annular slot-shaped cavity of the combustion chamber is alpha, and the included angle between the outer ring fuel injection channel and the inner wall of the annular slot-shaped cavity of the combustion chamber is 30-90 degrees.
Further, the combustion chamber assembly further comprises an inner fuel chamber rear section and an outer fuel chamber rear section, the inner fuel chamber rear section is an annular cavity formed by encircling an inner ring body and a combustion chamber, an outlet end of the inner fuel chamber front section and an inlet end of the inner fuel chamber rear section are communicated with each other, the outer fuel chamber rear section is an annular cavity formed by encircling a combustion chamber first shell and a combustion chamber second shell, and an outlet end of the inner fuel chamber front section and an inlet end of the inner fuel chamber rear section are communicated with each other.
Further, the combustion chamber assembly further comprises a connecting bolt, an outer ring fuel channel adjusting screw and an inner ring fuel injection channel adjusting screw, wherein the connecting bolt is arranged on the outlet side of the inner ring of the combustion chamber, the connecting bolt is adjusted to enable the inner ring of the combustion chamber and the first shell of the combustion chamber to axially move along the central axis, the inner ring fuel injection channel adjusting screw is arranged on the inner fuel cavity shell, the inner fuel cavity shell can be locked with the inner ring body through the inner ring fuel injection channel adjusting screw, the outer ring fuel channel adjusting screw is arranged on the second shell of the combustion chamber, and the second shell of the combustion chamber can be locked with the first shell of the combustion chamber through the outer ring fuel channel adjusting screw.
Further, binary channels detonation combustion chamber still includes oxidant steady voltage subassembly, oxidant steady voltage subassembly includes oxidant steady voltage chamber shell, external oxidizer pipe, oxidant injection chamber, oxidant steady voltage chamber and flow equalizing plate, oxidant steady voltage chamber shell sets up the import side at combustion chamber second shell, oxidant steady voltage chamber is the inside cavity of oxidant steady voltage chamber shell, external oxidizer pipe link up the outer wall that sets up at oxidant steady voltage chamber shell, oxidant steady voltage chamber is connected through flow equalizing plate and oxidant injection chamber, set up a plurality of oxidant flow equalizing holes on the flow equalizing plate.
Further, the combustion chamber assembly further comprises a necking, a nozzle throat and a nozzle spout, wherein the necking is arranged at the inlet end of the combustion chamber circular-slot-shaped cavity, the outlet end of the combustion chamber circular-slot-shaped cavity is connected to the nozzle spout through the nozzle throat, and the outlet end of the nozzle spout is communicated with the outside.
Further, the external fuel pipe is radially and vertically tangent to the front section of the inner fuel cavity, and the second external fuel pipe is radially and vertically tangent to the front section of the outer fuel cavity.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least:
The annular assembly reservation gap in the combustion chamber is adopted to connect the fuel cavity and the mixture combustion chamber, the processing spray holes are replaced, different assembly gaps are adopted, namely, the injection mixing section is controlled to adapt to different flow scene requirements, the swirl injection mode is matched, the processing injection problem of the current detonation annular seam combustion chamber is solved, the mixing problem is solved, the oxidant cavity adopts a structure with a pressure stabilizing cavity added, and the pressure stability is improved. The outer annular wall surface is used as a fuel injection cavity, the fuel cavity of the whole cavity in the inner annular body is removed, the annular seam type fuel injection cavity is changed into the annular seam type fuel injection cavity, the size of an annular body in the combustion chamber is reduced, the section of the whole combustion chamber is reduced, and the mass and the volume of the knocking combustion chamber are greatly reduced. The internal and external circular seams of the combustion chamber are adopted for swirl injection, so that the space utilization rate is improved, the overall weight is reduced, the fuel is injected at angles in two directions, the mixing effect of the oxidant and the fuel is better, and the flow can be obviously improved. The annular seam fuel cavities are integrated in the inner ring and the outer ring of the combustion chamber, the annular seam fuel cavities directly penetrate through the area of the combustion chamber, the heat of the combustion chamber is taken away by fuel flow, the temperature of the combustion chamber is reduced, the fuel is heated, the fuel reaches the temperature suitable for mixing combustion, an independent fuel heater is omitted, the service life of the detonation engine is prolonged, and the continuous working time is prolonged.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a radial cross-sectional view of a first embodiment of the present invention;
FIG. 2 is an axial cross-sectional view of portion A-A of FIG. 1;
FIG. 3 is a radial cross-sectional view of portion B-B of FIG. 2;
FIG. 4 is a radial cross-sectional view of portion C-C of FIG. 2;
FIG. 5 is a cross-sectional view of a first embodiment of the present invention;
fig. 6 is a perspective view of a first embodiment of the present invention;
FIG. 7 is a radial cross-sectional view of a second embodiment of the present invention;
FIG. 8 is an axial cross-sectional view of portion A-A of FIG. 7;
FIG. 9 is a radial cross-sectional view of portion B-B of FIG. 8;
FIG. 10 is a radial cross-sectional view of portion C-C of FIG. 8;
FIG. 11 is a cross-sectional view of a second embodiment of the present invention;
Fig. 12 is a perspective view of a second embodiment of the present invention;
FIG. 13 is an enlarged view of an inner ring fuel injection passage portion of an embodiment of the present invention;
FIG. 14 is an enlarged view of an outer ring fuel injection passage portion of an embodiment of the present invention.
Reference numerals illustrate: 1. a first external fuel tube; 2. An inner fuel cavity front section; 3. an oxidant plenum housing; 4. an oxidant plenum; 5. a flow equalizing plate; 6. oxidant flow homogenizing holes; 7. necking; 8. a combustion chamber second housing; 9. a combustion chamber circular slot-shaped cavity; 10. a combustion chamber first housing; 11. a nozzle throat; 12. a spray pipe nozzle; 13. a combustion chamber inner ring; 14. a connecting bolt; 15. an inner fuel cavity rear section; 16. an outer fuel chamber rear section; 17. an inner ring fuel injection passage; 18. an outer ring fuel injection passage; 19. an outer fuel chamber front section; 20. an outer fuel cavity inner housing; 21. an outer ring fuel passage adjustment screw; 22. externally connecting an oxidant tube; 23. an inner fuel cavity housing; 24. an inner ring body; 25. an oxidant injection chamber; 26. an inner ring fuel injection passage adjustment screw; 27. and a second external fuel pipe.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, apparatus may be implemented and/or methods practiced using any number and aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present application by way of illustration, and only the components related to the present application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The detonation combustors of the prior art suffer from several drawbacks:
1. Without a pressure stabilizing cavity, the pressure is partially reduced along with the injection process, and the pressure cannot be maintained, so that the actual mixing equivalent ratio is inaccurate, the stability is poor, and the generated thrust is unstable;
2. the current fuel interface only has a connecting function, the fuel is simply injected by pressure, the fuel interface only has the function of communicating an external fuel tank with a fuel cavity, and the fuel interface does not have other flow-assisting functions;
3. the fuel spray holes are formed by machining, so that the requirements on cutters are high, the loss is high, the machining is time-consuming and labor-consuming, and the cost is high;
4. The size of the fuel channel is not adjustable, the influence of the size of the fuel channel on the performance is not good, the research of different spray hole types needs repeated assembly, and the period is long;
5. the heat energy can not be fully and sufficiently converted into the kinetic energy of the fuel gas without the shrinkage and expansion spray pipe or the shrinkage and expansion spray pipe, so that the heat energy is converted into the thrust, and the efficiency is low;
6. the design of the inner ring full cavity is adopted for the fuel, and the size of the cavity is designed to be larger according to the requirements of pressure maintaining and flow, so that the occupied space is larger.
7. The fuel is sprayed from the inner ring column cavity in a single channel, and the mixing effect is uneven at the other side of the oxidant;
8. The cooling mode of the combustion chamber area is mainly water cooling or air film cooling, and all the cooling mediums except the oxidant and the fuel are required to be independently connected, and a matched independent supply system and a pipeline are required to be carried, so that the structure is relatively complex, the cost is relatively high, and the arrangement space is large; the gas film cooling gas directly enters the combustion chamber and is mixed with the combustible mixed gas, the mixing proportion of the combustible gas is influenced, the influence degree on combustion is not thoroughly studied, the combustible gas is diluted by the cooling gas, and the combustion efficiency is most likely to be influenced. The existing method basically carries out independent external cooling medium cooling on the outer shell of the combustion chamber, and has insufficient cooling effect on the wall surface of the outer shell of the combustion chamber and the wall surface of the inner ring of the combustion chamber, which are directly contacted with the circumferential seam of the combustion chamber.
The following describes the technical scheme provided by each embodiment of the present application with reference to the accompanying drawings.
Fig. 1 to 6 illustrate an embodiment of the present application.
The first embodiment provides a dual-channel detonation combustor which replaces the existing combustor scheme, and is provided with a pressure stabilizing cavity, so that the supply pressure of the dual-channel detonation combustor is kept stable, and the performance of the dual-channel detonation combustor is stable; the fuel cavity is designed on the shell of the combustion chamber and is symmetrically sprayed on the oxidant for mixing with the inner ring column in a double-channel mode, then the fuel cavity is externally connected with the fuel channel to form a rotational flow type auxiliary flow, a rotational flow effect can be generated under the pressure, and the fuel cavity enters the combustion chamber in a rotational posture and is better mixed with the oxidant; the gap type fuel supply channel is assembled to replace a machined fuel injection hole, and the gap width of the fuel supply channel can be adjusted within the range of more than or equal to 0.01mm by adjusting the assembly gap, so that the annular slot type Laval nozzle is formed by assembling the inner ring and the outer ring of the combustion chamber, the nozzle and the inner shell of the combustion chamber are designed into an integrated mode, the air injection speed is improved, and the thrust conversion is enhanced. By adopting the fuel double-channel injection, under the condition of smaller inner ring body, the combustion chamber shell is provided with a fuel injection channel, the flow of fuel is not influenced, the whole quality is lighter, and atomization is better.
As shown in fig. 1,2, 5 and 6, the outer ring detonation combustor of the dual-channel detonation combustor is composed of a combustor housing assembly, a combustor assembly and an oxidant pressure stabilizing assembly.
The combustion chamber housing assembly comprises a combustion chamber inner ring group, a fuel cavity housing and a combustion chamber housing which are sequentially sleeved from inside to outside. The combustion chamber inner ring group includes a combustion chamber inner ring 13. The combustion chamber housing comprises a combustion chamber second housing 8. The fuel cavity outer shell comprises an inner fuel cavity outer shell 23 and an outer fuel cavity inner shell 20 which are sleeved in sequence from inside to outside.
The combustion chamber assembly comprises an oxidant injection chamber 25, a combustion chamber annular slot-shaped chamber 9, a first external fuel pipe 1, an inner fuel chamber front section 2, an outer fuel chamber front section 19, a second external fuel pipe 27, an inner annular fuel injection passage 17 and an outer annular fuel injection passage 18. The inner fuel cavity outer shell 23 and the outer fuel cavity inner shell 20 are surrounded to form an oxidant injection cavity 25, and the inlet end of the combustion chamber annular slit-shaped cavity 9 and the outlet end of the oxidant injection cavity 25 are mutually communicated. The combustion chamber inner ring 13 and the inner fuel chamber housing 23 are surrounded to form an inner fuel chamber front section 2, and the first external fuel pipe 1 is arranged on the outer wall of the inner fuel chamber housing 23 and is communicated with the inner fuel chamber front section 2. The combustion chamber second outer shell 8 and the outer fuel chamber inner shell 20 are surrounded to form an outer fuel chamber front section 19, and a second external fuel pipe 27 is arranged on the outer wall of the combustion chamber second outer shell 8 and communicated with the outer fuel chamber front section 19. The inner ring fuel injection passage 17 is used to communicate the inner fuel cavity front section 2 with the combustion chamber annular slot-shaped cavity 9, and the outer ring fuel injection passage 18 is used to communicate the outer fuel cavity front section 19 with the combustion chamber annular slot-shaped cavity 9.
The oxidant pressure stabilizing cavity 4 consists of an external oxidant tube 22, an oxidant pressure stabilizing cavity shell 3, an oxidant flow equalizing hole 6, a flow equalizing plate 5 and an internal combustion cavity shell 23, the oxidant pressure stabilizing cavity 4 is additionally arranged, so that the pressure of the oxidant flowing from the external oxidant tube 22 is more stable, the problem of unstable flowing pressure caused by consumption of the oxidant is solved, meanwhile, the oxidant flow equalizing hole 6 is designed between the oxidant pressure stabilizing cavity 4 and the oxidant injecting cavity 25, the oxidant can be distributed to the oxidant injecting cavity 25 more uniformly in the circumferential direction, and then the oxidant is injected from the shrinkage 7 uniformly, and fuel injected from the nozzle front section, the internal annular fuel injecting channel 17 and the external annular fuel injecting channel 18 are mixed to form a fully mixed combustible mixture, and enter the combustion chamber annular slot-shaped cavity 9, so that good ignition conditions are created for knocking; after being mixed and spread at a small distance in the front section of the combustion chamber, the combustible material is ignited by an igniter arranged on the second shell 8 of the combustion chamber, the combustible material forms a matched annular spray pipe with the inner ring 13 of the combustion chamber (namely the tail end of the combustion chamber) through the second shell 8 of the combustion chamber, the annular spray pipe comprises a spray pipe throat 11 and a spray pipe nozzle 12, and high-temperature and high-pressure products are sprayed out in an accelerating way to form thrust, and the spray pipe is integrated in the contours designed in the second shell 8 of the combustion chamber and the inner ring 13 of the combustion chamber. Because the fuel cavity is integrated into the space of the combustion chamber housing, the overall size of the combustion chamber is relatively small with the same thrust force, reducing the separate design of the nozzle and mounting interface.
The inner ring fuel injection channel 17 (assembly gap forming) and the outer ring fuel injection channel 18 (assembly gap forming) are formed by circumferential gaps formed by assembly, and the traditional design adopts a fuel spray hole design and is formed by machining, so that the requirements on cutters are high, the loss is high, the machining is time-consuming and labor-consuming, and the cost is high. As shown in fig. 13, the injection effect is good when the included angle between the injection direction of the inner ring fuel injection channel 17 and the injection port interface is θ, and θ is between 30 ° and 90 °. As shown in fig. 14, the injection effect is better when the included angle between the injection direction of the outer ring fuel injection channel 18 and the injection port interface is alpha, and alpha is between 30 and 90 degrees. The sizes of the inner ring fuel injection channel 17 and the outer ring fuel injection channel 18 are adjusted by adjusting the axial positions of the second shell 8 of the combustion chamber and the outer shell 23 of the inner combustion chamber, and the adjusted positions are locked by the outer ring fuel channel adjusting screw 21 and the inner ring fuel injection channel adjusting screw 26. The aperture of the traditional injection hole is not adjustable, so that the method has important significance for researching the change relation of the injection area and the flow, and provides a new idea for the subsequent design of the variable thrust detonation engine.
As shown in fig. 3, the first external fuel pipe 1 is designed to be perpendicular to the circumferential seam of the inner fuel cavity front section 2, and has a diagonally tangential structure, and when fuel is connected to the inner fuel cavity front section 2 through the first external fuel pipe 1, a swirling effect is generated, and the fuel is pushed to one side of the inner ring fuel injection passage 17 (assembly gap formation), and is rotationally ejected from the inner ring fuel injection passage 17 (assembly gap formation) in a circumferentially discrete state in cooperation with extrusion of pressure, and sufficiently mixed with the oxidant flowing out from the constriction 7 in an accelerating manner.
As shown in fig. 4, the second external fuel pipe 27 is designed to be perpendicular to the circumferential seam of the front section 19 of the external fuel cavity, and is in a diagonally tangential structure, when the fuel is connected to the front section 19 of the external fuel cavity through the second external fuel pipe 27, a swirling effect is generated, the external fuel injection channel 18 is pushed on one side, and the external fuel injection channel 18 is rotated and ejected in a circumferentially discrete state (formed by assembly gaps) by extrusion under pressure, so that the external fuel injection channel 18 is fully mixed with the oxidant accelerated and flowed out from the necking 7. Compared with the design without a tangential external fuel pipe, the design has the advantages that the mixing efficiency is obviously improved, the axial distance required by the full mixing of the mixed gas is shorter, the length of a combustion chamber of the detonation engine is reduced, the weight is reduced, the specific impulse is improved, and the design of the dual-fuel injection channel ensures that the flow is not influenced under the condition that the design of an inner ring body is smaller, and the mixed gas is more fully mixed with the oxidant at double angles. The conventional fuel channel is designed into a fuel cavity structure independently or integrated in a combustion chamber ring body, the design of the whole cavity is realized, the space occupied by the ring body in the combustion chamber is large, a certain size is needed to ensure the pressure stability and the flow requirement of fuel, the outer wall of the combustion chamber is designed into an outer fuel cavity in a hollow mode, the original wall thickness of the outer wall is kept, and the weight can be reduced, and the volume of the combustion chamber can be reduced.
As shown in fig. 5, a plurality of oxidant flow equalizing holes 6 are provided on the flow equalizing plate 5.
After the combustion working state is finished, fuel supply is stopped, an inert gas nozzle electromagnetic valve of an external fuel pipeline is electrified to start working, gas sweeps a fuel cavity, excessive fuel is cleaned, the wall surface of the combustion chamber is cooled briefly, and a complete working cycle is finished.
The first embodiment integrally designs the outer fuel cavity front section 19 and the inner fuel cavity front section 2 to the combustion chamber housing and the reduced inner annular body 24 and is designed in a circular seam shape, and replaces the traditional inner shell or the full cavity design of the individual fuel module by matching with the first external fuel pipe 1 with the angular symmetry tangential direction. The traditional full-cavity design needs a certain arrangement space, occupies a large space, only depends on the pressure to extrude the fuel atomization effect to the downstream, and is controlled by improving the pressure; the oxidant adopts the oxidant pressure stabilizing cavity 4 and the flow equalizing plate 5, thereby achieving the purposes of stabilizing flow and equalizing flow and improving the traditional self-flowing mixing mode; the inner ring fuel injection channel 17 and the outer ring fuel injection channel 18 are assembled, the size is adjustable, the size is not limited by the thickness of materials, the traditional injection channel adopts an injection hole design, the diameter of the injection hole is also in the range of phi 0.1 mm-0.8 mm, after the diameter of the injection hole is smaller than phi 0.3mm, the machining is relatively difficult, the materials are generally made of stainless steel, the inclination of the materials with the wall thickness of 5mm is basically not machinable, other materials such as laser drilling have requirements on the wall thickness, the wall thickness is generally about 1mm, a plurality of workpieces are required to be machined according to different injection hole test schemes, and the cost for batch comparison test is obviously reduced; compared with a single spray pipe mode, the integrated spray pipe design of the combustion chamber omits installation and fewer parts, and ensures the quality control.
Fig. 7 to 12 show another embodiment of the present application.
The second embodiment provides a dual-channel detonation combustor which replaces the existing combustor scheme, and is provided with a pressure stabilizing cavity, so that the supply pressure of the dual-channel detonation combustor is kept stable, and the performance of the dual-channel detonation combustor is stable; the fuel cavity is designed on the shell of the combustion chamber and is symmetrically sprayed on the oxidant for mixing with the inner ring column in a double-channel mode, then the fuel cavity is externally connected with the fuel channel to form a rotational flow type auxiliary flow, a rotational flow effect can be generated under the pressure, and the fuel cavity enters the combustion chamber in a rotational posture and is better mixed with the oxidant; the gap type fuel supply channel is assembled to replace a machined fuel injection hole, and the gap width of the fuel supply channel can be adjusted within the range of more than or equal to 0.01mm by adjusting the assembly gap, so that the annular slot type Laval nozzle is formed by assembling the inner ring and the outer ring of the combustion chamber, the nozzle and the inner shell of the combustion chamber are designed into an integrated mode, the air injection speed is improved, and the thrust conversion is enhanced. By adopting the fuel double-channel injection, under the condition of smaller inner ring body, the combustion chamber shell is provided with a fuel injection channel, the flow of fuel is not influenced, the whole quality is lighter, and atomization is better. The combustion chamber is a self-cooling structure of the circular seam of the outer shell of the combustion chamber, the double-circular seam fuel cavity is communicated with the main combustion area of the detonation combustion chamber, but the wall surface of the circular seam cavity of the combustion chamber is not directly cooled, the combustion of the detonation combustion chamber is not influenced, the fuel carried by the combustion chamber can be utilized to cool the inner wall surface of the combustion chamber, and meanwhile, the fuel can be heated to a temperature at which the fuel is easier to atomize and burn. The dual channel cooling provides sufficient operating temperature to the detonation combustor materials to be stable and suitable for operation.
As shown in fig. 7, 8, 11 and 12, the dual-channel detonation combustor outer ring detonation combustor is composed of a combustor housing assembly, a combustor assembly and an oxidant plenum assembly.
The combustion chamber housing assembly comprises a combustion chamber inner ring group, a fuel cavity housing and a combustion chamber housing which are sequentially sleeved from inside to outside. The combustion chamber inner ring group comprises an inner ring body 24 and a combustion chamber inner ring 13 which are sleeved in sequence from inside to outside. The combustion chamber housing comprises a combustion chamber second housing 8, and the fuel chamber housing comprises an inner fuel chamber housing 23 and an outer fuel chamber inner housing 20 which are sleeved in sequence from inside to outside.
The combustion chamber assembly comprises an oxidant injection chamber 25, a combustion chamber annular slot-shaped chamber 9, a first external fuel pipe 1, an inner fuel chamber front section 2, an outer fuel chamber front section 19, a second external fuel pipe 27, an inner annular fuel injection passage 17 and an outer annular fuel injection passage 18. The inner fuel cavity outer shell 23 and the outer fuel cavity inner shell 20 are surrounded to form an oxidant injection cavity 25, and the inlet end of the combustion chamber annular slit-shaped cavity 9 and the outlet end of the oxidant injection cavity 25 are mutually communicated. The combustion chamber inner ring 13 and the inner fuel chamber housing 23 are surrounded to form an inner fuel chamber front section 2, and the first external fuel pipe 1 is arranged on the outer wall of the inner fuel chamber housing 23 and is communicated with the inner fuel chamber front section 2. The combustion chamber second outer shell 8 and the outer fuel chamber inner shell 20 are surrounded to form an outer fuel chamber front section 19, and a second external fuel pipe 27 is arranged on the outer wall of the combustion chamber second outer shell 8 and communicated with the outer fuel chamber front section 19. The inner ring fuel injection passage 17 is used to communicate the inner fuel cavity front section 2 with the combustion chamber annular slot-shaped cavity 9, and the outer ring fuel injection passage 18 is used to communicate the outer fuel cavity front section 19 with the combustion chamber annular slot-shaped cavity 9.
As shown in fig. 8 and 9, the circumferential seam between the first external fuel pipe 1 and the front section 2 of the internal fuel cavity is designed to be vertical and in a diagonally tangential structure, when a part of fuel is connected to the front section 2 of the internal fuel cavity through the first external fuel pipe 1, a swirl effect is generated, and the fuel is pushed to one side of an internal ring fuel injection channel 17 (formed by an assembly gap) and is rotationally ejected from the internal ring fuel injection channel 17 (formed by the assembly gap) in a circumferentially discrete state by extrusion of the matched pressure, so that the fuel is fully mixed with the oxidant which flows out from the necking 7 in an accelerating manner; the other part of fuel is filled in the rear section 15 (cooling cavity) of the inner fuel cavity, the rear section 15 (cooling cavity) of the inner fuel cavity is formed by encircling the inner ring body 24 and the inner ring 13 of the combustion chamber, the fuel filled in the rear section of the inner fuel cavity is used as a coolant for cooling the inner wall of the combustion chamber, hot oil after heat exchange flows back to the new fuel for secondary heat exchange, the newly injected fuel is heated, the inner ring fuel injection channel 17 (formed by assembly gaps) enters the combustion chamber for combustion, and the inner wall surface of the combustion chamber is continuously cooled along with the continuous entering of the new fuel into the annular gap fuel cavity, so that the self-cooling purpose of the detonation combustion chamber is achieved, the reliability of the engine is improved, and the single-time working time length is prolonged.
As shown in fig. 8 and 10, the second external fuel pipe 27 is formed in a vertical and diagonally tangential structure with respect to the circumferential seam of the external fuel chamber front section 19, and when the fuel is introduced into the external fuel chamber front section 19 through the second external fuel pipe 27, a swirling effect is generated, and the external fuel injection passage 18 (assembly gap formation) is pushed to one side, and the fuel is rotationally ejected from the external fuel injection passage 18 (assembly gap formation) in a circumferentially discrete state by being pressed by a pressure, so that the fuel is sufficiently mixed with the oxidant flowing out from the constriction 7 in an accelerated manner. Compared with the design without a tangential external fuel pipe, the design has the advantages that the mixing efficiency is obviously improved, the axial distance required by the full mixing of the mixed gas is shorter, the length of a combustion chamber of the detonation engine is reduced, the weight is reduced, the specific impulse is improved, and the design of the dual-fuel injection channel ensures that the flow is not influenced under the condition that the design of the inner ring body 24 is smaller, and the mixed gas is more fully mixed with the oxidant at double angles. The outer fuel cavity rear section 16 (self-cooling combustion chamber) is formed by encircling a combustion chamber second housing 8 and a combustion chamber first housing, the outer fuel cavity rear section 16 is of a circular seam structure coaxial with a combustion chamber circular seam-shaped cavity 9, and can cool the inner wall of the combustion chamber, and the principle is as follows: through combustion chamber shell circumferential seam self-cooling structure, the circumferential seam fuel chamber link up to the knocking combustion chamber main combustion zone, can utilize the fuel that carries of itself, carries out cooling for the combustion chamber internal wall face, and the fuel can be heated to the temperature of being heated to easier atomizing and burning simultaneously, along with the impact of new fuel, constantly takes away the heat, lets the stable work of combustion chamber for a long time. The conventional fuel channel is designed into a fuel cavity structure independently or integrated in a combustion chamber ring body, the design of the whole cavity is realized, the space occupied by the ring body in the combustion chamber is large, a certain size is needed to ensure the pressure stability and the flow requirement of fuel, the outer wall of the combustion chamber is designed into an outer fuel cavity in a hollow mode, the original wall thickness of the outer wall is kept, and the weight can be reduced, and the volume of the combustion chamber can be reduced.
The inner ring fuel injection channel 17 (assembly gap forming) and the outer ring fuel injection channel 18 (assembly gap forming) are formed by circumferential gaps formed by assembly, and the traditional design adopts a fuel spray hole design and is formed by machining, so that the requirements on cutters are high, the loss is high, the machining is time-consuming and labor-consuming, and the cost is high. As shown in fig. 13, the injection effect is good when the included angle between the injection direction of the inner ring fuel injection channel 17 and the injection port interface is θ, and θ is between 30 ° and 90 °. As shown in fig. 14, the injection effect is better when the included angle between the injection direction of the outer ring fuel injection channel 18 and the injection port interface is alpha, and alpha is between 30 and 90 degrees. The sizes of the inner ring fuel injection channel 17 and the outer ring fuel injection channel 18 are adjusted by adjusting the axial positions of the combustion chamber second outer shell 8, the combustion chamber first outer shell 10 and the outer fuel cavity inner shell 20, the combustion chamber inner ring 13, the inner ring body 24 and the inner fuel cavity outer shell 23, and the adjustment is locked by the outer ring fuel channel adjustment screw 21 and the inner ring fuel injection channel adjustment screw 26. The aperture of the traditional injection hole is not adjustable, so that the method has important significance for researching the change relation of the injection area and the flow, and provides a new idea for the subsequent design of the variable thrust detonation engine.
The oxidant pressure stabilizing cavity 4 consists of an external oxidant tube 22, an oxidant pressure stabilizing cavity shell 3, an oxidant flow equalizing hole 6, a flow equalizing plate 5 and an internal combustion cavity shell 23, the oxidant pressure stabilizing cavity 4 is additionally arranged, so that the pressure of the oxidant flowing from the external oxidant tube 22 is more stable, the problem of unstable flowing pressure caused by consumption of the oxidant is solved, meanwhile, the oxidant flow equalizing hole 6 is designed between the oxidant pressure stabilizing cavity 4 and the oxidant injecting cavity 25, the oxidant can be distributed to the oxidant injecting cavity 25 more uniformly in the circumferential direction, and then the oxidant is injected from the shrinkage 7 uniformly, and fuel injected from the nozzle front section, the internal annular fuel injecting channel 17 and the external annular fuel injecting channel 18 are mixed to form a fully mixed combustible mixture, and enter the combustion chamber annular slot-shaped cavity 9, so that good ignition conditions are created for knocking; after being mixed and spread at a small distance in the front section of the combustion chamber, the combustible is ignited by an igniter arranged on the first shell 10 of the combustion chamber, the combustible forms a matched annular spray pipe with the inner ring 13 of the combustion chamber, namely the tail end of the combustion chamber, the annular spray pipe comprises a spray pipe throat 11 and a spray pipe nozzle 12, the high-temperature and high-pressure product is sprayed out in an accelerating way to form thrust, and the spray pipe is integrated in the contours designed in the first shell 10 of the combustion chamber and the inner ring 13 of the combustion chamber. Because the fuel cavity is integrated into the space of the combustion chamber housing, the overall size of the combustion chamber is relatively small with the same thrust force, reducing the separate design of the nozzle and mounting interface.
As shown in fig. 11, a plurality of oxidant flow equalizing holes 6 are provided on the flow equalizing plate 5.
After the combustion working state is finished, fuel supply is stopped, an inert gas nozzle electromagnetic valve of an external fuel pipeline is electrified to start working, gas sweeps a fuel cavity, excessive fuel is cleaned, the wall surface of the combustion chamber is cooled briefly, and a complete working cycle is finished.
The second embodiment integrates the outer fuel cavity front section 19 and the inner fuel cavity front section 2 into the combustion chamber housing and the reduced inner ring body 24, and is designed into a circular seam shape, the dual fuel cavity penetrates into the main combustion chamber area (cooling effect) and is matched with the first external fuel pipe 1 with symmetrical and tangential angles to replace the traditional inner housing or the full-cavity design of the independent fuel module. The traditional full-cavity design needs a certain arrangement space, occupies a large space, only depends on the pressure to extrude the fuel atomization effect to the downstream, and is controlled by improving the pressure; the oxidant adopts a pressure stabilizing cavity and a flow equalizing plate, thereby achieving the purposes of stabilizing flow and equalizing flow and improving the traditional self-flowing mixing mode; the inner ring fuel injection channel 17 and the outer ring fuel injection channel 18 are assembled, the size is adjustable, the limitation of the thickness of materials is avoided, the traditional injection channel adopts an injection hole design, the diameter of the injection hole is also in the range of phi 0.1 mm-0.8 mm, after the diameter of the injection hole is smaller than phi 0.3mm, the machining is relatively difficult, the material is generally made of stainless steel, the inclination of the material with the wall thickness of 5mm is basically not machinable, other materials such as laser drilling have requirements on the wall thickness, the wall thickness is generally about 1mm, a plurality of workpieces are required to be machined according to different injection hole test schemes, and the cost for batch comparison test is obviously reduced; compared with a single spray pipe mode, the integrated spray pipe design of the combustion chamber omits installation and fewer parts, and ensures the quality control. Through the fuel flow penetrating to the knocking main combustion area, part of heat transferred to the inner wall of the combustion chamber is taken away, forced cooling is carried out, the wall surface is cooled, and the service life of parts is prolonged.
In this specification, each embodiment is described in a progressive manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment focuses on differences from other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is relatively simple, and reference should be made to the description of some of the system embodiments.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (6)
1. A dual channel detonation combustor, comprising:
The combustion chamber shell assembly comprises a combustion chamber inner ring group, a fuel cavity shell and a combustion chamber shell which are coaxial and are sequentially sleeved from inside to outside;
The combustion chamber inner ring group comprises an inner ring body (24) and a combustion chamber inner ring (13), the combustion chamber inner ring (13) is coaxially sleeved outside the inner ring body (24), the combustion chamber outer shell comprises a combustion chamber first shell (10) and a combustion chamber second shell (8), the combustion chamber second shell (8) is coaxially sleeved outside the combustion chamber first shell (10), the fuel cavity outer shell comprises an inner fuel cavity outer shell (23) and an outer fuel cavity inner shell (20), and the outer fuel cavity inner shell (20) is coaxially sleeved outside the inner fuel cavity outer shell (23);
The combustion chamber assembly comprises an inner fuel cavity rear section (15), an outer fuel cavity rear section (16), an oxidant injection cavity (25), a combustion chamber annular slit-shaped cavity (9), a first external fuel pipe (1), an inner fuel cavity front section (2), an outer fuel cavity front section (19) and a second external fuel pipe (27), the oxidant injection cavity (25) is an annular cavity formed by surrounding the fuel cavity housing and the combustion chamber housing, the inlet end of the combustion chamber annular slit-shaped cavity (9) and the outlet end of the oxidant injection cavity (25) are communicated with each other, the inner fuel cavity front section (2) is an annular cavity formed by combining the fuel cavity housing and the combustion chamber annular slit-shaped cavity, the first external fuel pipe (1) is arranged on the outer wall of the fuel cavity housing and is communicated with the fuel cavity front section (2), the outer fuel cavity front section (19) is arranged on the radial outer side of the oxidant injection cavity (25), the second external fuel pipe (27) is communicated with the outer fuel cavity front section (19), the inner fuel cavity front section (19) and the combustion chamber front section (9) and the combustion chamber front section (13) and the combustion chamber inner fuel cavity front section (2) are communicated with the inner fuel cavity (15) and the combustion chamber front section (13), the outer fuel cavity rear section (16) is an annular cavity formed by encircling the first combustion chamber shell (10) and the second combustion chamber shell (8), the outlet end of the inner fuel cavity front section (2) and the inlet end of the inner fuel cavity rear section (15) are communicated with each other, fuel in the inner fuel cavity rear section (15) is used for cooling the inner ring group of the combustion chamber, fuel in the outer fuel cavity rear section (16) is used for cooling the combustion chamber shell, the inner fuel cavity rear section (15) and the outer fuel cavity rear section (16) are communicated to a main combustion area of the detonation combustion chamber, and the inner fuel cavity rear section (15) and the outer fuel cavity rear section (16) are filled with flowing fuel when the combustion chamber works;
The combustion chamber assembly further comprises an inner ring fuel injection channel (17), wherein the inner ring fuel injection channel (17) is an axial gap between an inner fuel cavity shell (23) and a combustion chamber inner ring (13), an inlet end of the inner ring fuel injection channel (17) is connected with the front section (2) of the inner fuel cavity, and an outlet end of the inner ring fuel injection channel (17) is connected with the annular slit-shaped cavity (9) of the combustion chamber;
The combustion chamber assembly further comprises an outer ring fuel injection channel (18), wherein the outer ring fuel injection channel (18) is an axial gap between an inner shell (20) of the outer fuel cavity and a first shell (10) of the combustion chamber, an inlet end of the outer ring fuel injection channel (18) is connected with a front section (19) of the outer fuel cavity, and an outlet end of the outer ring fuel injection channel (18) is connected with a circular slot-shaped cavity (9) of the combustion chamber;
The combustion chamber assembly further comprises a connecting bolt (14), an outer ring fuel channel adjusting screw (21) and an inner ring fuel injection channel adjusting screw (26), wherein the connecting bolt (14) is arranged on the outlet side of the combustion chamber inner ring (13), the connecting bolt (14) is adjusted to enable the combustion chamber inner ring (13) and the combustion chamber first shell (10) to axially move along the central axis, the inner ring fuel injection channel adjusting screw (26) is arranged on the inner fuel cavity shell (23), the inner fuel cavity shell (23) can be locked through the inner ring fuel injection channel adjusting screw (26) and the inner ring body (24), the outer ring fuel channel adjusting screw (21) is arranged on the combustion chamber second shell (8), and the combustion chamber second shell (8) can be locked through the outer ring fuel channel adjusting screw (21) and the combustion chamber first shell (10);
The dual-channel detonation combustion chamber further comprises an oxidant pressure stabilizing component, the oxidant pressure stabilizing component comprises an oxidant pressure stabilizing cavity shell (3), an external oxidant pipe (22), an oxidant injection cavity (25), an oxidant pressure stabilizing cavity (4) and a flow equalizing plate (5), the oxidant pressure stabilizing cavity shell (3) is arranged on the inlet side of a combustion chamber second shell (8), the oxidant pressure stabilizing cavity (4) is a cavity inside the oxidant pressure stabilizing cavity shell (3), the external oxidant pipe (22) is communicated with the outer wall of the oxidant pressure stabilizing cavity shell (3), the oxidant pressure stabilizing cavity (4) is connected with the oxidant injection cavity (25) through the flow equalizing plate (5), and a plurality of oxidant flow equalizing holes (6) are formed in the flow equalizing plate (5).
2. The dual-channel detonation combustor as claimed in claim 1 wherein the outer fuel cavity front section (19) is an annular cavity formed by the surrounding of the first combustion chamber housing (10) and the second combustion chamber housing (8), the second external fuel pipe (27) is arranged on the outer wall of the second combustion chamber housing (8), the inner fuel cavity front section (2) is an annular cavity formed by the surrounding of the inner fuel cavity housing (23) and the inner ring body (24), and the first external fuel pipe (1) is arranged on the outer wall of the inner fuel cavity housing (23).
3. The dual channel detonation combustor of claim 1 wherein the inner annular fuel injection channel (17) is at an angle θ of 30 ° to 90 ° to the inner wall of the combustor annular slot-shaped cavity (9).
4. The dual channel detonation combustor of claim 1, wherein the outer ring fuel injection channel (18) is at an angle α of 30 ° to 90 ° to the inner wall of the combustor annular slot-shaped cavity (9).
5. The dual channel detonation combustor of claim 1, wherein the combustor assembly further comprises a constriction (7), a nozzle throat (11) and a nozzle spout (12), the constriction (7) is disposed at an inlet end of the combustor annular slit-shaped chamber (9), an outlet end of the combustor annular slit-shaped chamber (9) is connected to the nozzle spout (12) through the nozzle throat (11), and an outlet end of the nozzle spout (12) is in communication with the outside.
6. The dual channel detonation combustor of claim 1, wherein the first circumscribing fuel tube (1) is radially and vertically tangential to the inner fuel cavity front section (2) and the second circumscribing fuel tube (27) is radially and vertically tangential to the outer fuel cavity front section (19).
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