CN115342382A

CN115342382A - Single-channel oxygen supply detonation combustion chamber module and detonation combustion chamber

Info

Publication number: CN115342382A
Application number: CN202210887355.1A
Authority: CN
Inventors: 韦焕程; 董琨; 高宗永; 刘海洋
Original assignee: Qinghang Aerospace Beijing Technology Co ltd
Current assignee: Qinghang Aerospace Beijing Technology Co ltd
Priority date: 2022-07-26
Filing date: 2022-07-26
Publication date: 2022-11-15

Abstract

The invention provides a single-channel oxygen supply detonation combustor module and a detonation combustor. The detonation combustor is formed from a plurality of detonation combustor modules and cooperates with an ignition assembly. The detonation engine with the structural design of the multi-annular-seam combustion chamber expands the adjustable range of the thrust, controls the change of the thrust by combining the working states of the multiple combustion chambers, has a simple and effective control system, and realizes the rapid and accurate adjustment and control of the wide-range thrust; the combustion chamber is designed along with the appearance of the aircraft, so that the utilization rate of space is improved; the combustion chamber adopts multi-channel fuel supply, which is not affected mutually, stable and safe; the structure of the oxidant supply channel is simple, the supply of the oxidant is one way, the ignition of a multi-ring combustion chamber is realized, the oxidant still passes through the combustion chamber which does not work, and the cooling protection is provided for the adjacent combustion chambers.

Description

Single-channel oxygen supply detonation combustion chamber module and detonation combustion chamber

Technical Field

The specification relates to the technical field of detonation combustors, in particular to a single-channel oxygen supply detonation combustor module and a detonation combustor.

Background

The slow combustion and detonation combustion modes exist in nature, the propagation rate of flame of the slow combustion is relatively low, and the combustion modes in power devices such as an internal combustion engine, an aircraft engine, a gas turbine and the like are all slow combustion; detonation combustion is characterized in that the upstream of a combustion area is of a shock wave structure, shock waves are coupled with the combustion area to propagate, and the flame propagation speed of detonation combustion is far higher than that of slow combustion and can reach thousands of meters per second generally.

In recent years, with the continuous and deep research on hypersonic aircrafts and single-stage in-orbit power systems, the technology of novel continuous rotation detonation engines is rapidly developed. Researches show that the propelling technology based on detonation combustion can greatly reduce fuel consumption, greatly improve the specific impulse characteristic of a power device and has important significance for widening the working envelope of the air-breathing aircraft and improving the economy and the operational performance of the conventional weaponry. As a leading technology capable of overtaking at a curve, comprehensive and deep research on the technology is more urgent.

The continuous rotation detonation engine is a power technology utilizing detonation combustion, and has the following characteristics and advantages in summary: 1. only one time of successful detonation is needed, and the detonation wave can be continuously transmitted along the circumferential direction of the combustion chamber; 2. the combustion rate is high, the heat release intensity is high, the structure of the combustion chamber is compact, and the length of the engine can be shortened; 3. the boosting characteristic is provided, the number of stages of a compressor of the turbine engine can be reduced or the total pressure loss of an air inlet passage of the ramjet engine can be reduced, the design of a propulsion system can be simplified, and the thrust-weight ratio of the engine can be improved; 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 high Mach number supersonic speed. Therefore, the research of the continuous rotation knocking engine gradually draws a great deal of attention in the scientific field.

The current single-crack detonation combustion chamber (punching or rocket or combination) detonation engine has the problems of insufficient thrust, difficulty in realizing simple, accurate and efficient control of the thrust, low space utilization rate of the single-crack detonation combustion chamber, difficulty in variable thrust control and the like. The current detonation engine only has a single combustion chamber, the cross section shape is mostly circular seam type, the central space can not be fully utilized, and the control of the output thrust by changing the rotating speed can not be realized like other power devices such as a turbojet engine or an internal combustion engine under the condition that the supply parameters of fuel and oxidant are constant. The change of the thrust can only be controlled by an equivalence ratio at present, but the flow rate of the single-ring-slit combustion chamber for realizing stable combustion cannot be infinitely increased or reduced, so the controllable domain of the thrust is narrow.

At present, a lot of achievements and a lot of experiences are obtained and accumulated in the research of the continuous rotation detonation engine, but the problems that the research on the combustion controllability and the variable thrust and the like is not thorough are gradually exposed, the barrier on the engineering road is more prominent, and the key problem of overcoming the above key problems is more critical to the final application of the continuous rotation detonation engine. The research on the minimum section, the minimum length, the maximum specific impulse and the minimum volume of the detonation combustion chamber also starts the propelling of a compact drum, and the research on the detonation engine integrating a multi-annular-seam detonation combustion chamber is a simple and feasible idea. However, the inner ring body is reduced or increased, the number is increased, the fuel flow is correspondingly reduced, and the fuel multi-channel injection and oxidant single-channel injection inlet shunting are one of the research directions.

Disclosure of Invention

In view of this, the embodiments of the present disclosure provide a single-channel oxygen supply detonation combustor module and a detonation combustor, which achieve the effects of multi-channel fuel supply and precise thrust control through a modular structure.

The embodiment of the specification provides the following technical scheme:

a single channel oxygen supply detonation combustor module, comprising:

the combustion chamber assembly comprises a circular seam combustion chamber, an inner ring body and a combustion chamber shell which are coaxial and are sequentially sleeved from inside to outside, and the circular seam combustion chamber is an annular cavity formed by the surrounding of the combustion chamber shell and the inner ring body;

the oxidant supply assembly comprises an oxidant inlet, an oxidant inlet cavity shell, an oxidant pressure stabilizing cavity, an oxidant distribution inlet of a circumferential seam combustion chamber, an oxidant flow equalizing plate and an oxidant distribution cavity outer cover plate, wherein the oxidant inlet is arranged on the outer wall of the oxidant inlet cavity shell in a penetrating manner, the oxidant pressure stabilizing cavity is a cavity in the oxidant inlet cavity shell, one end of the oxidant distribution inlet of the circumferential seam combustion chamber is communicated with the oxidant pressure stabilizing cavity, the other end of the oxidant distribution inlet of the circumferential seam combustion chamber is communicated with the oxidant distribution cavity outer cover plate, the oxidant distribution cavity outer cover plate is communicated with the oxidant flow equalizing plate, an oxidant flow equalizing circumferential seam is arranged between the oxidant flow equalizing plate and the circumferential seam combustion, and one oxidant pressure stabilizing cavity is correspondingly communicated with the circumferential seam combustion chamber through the circumferential seam combustion chamber oxidant distribution inlet, the oxidant distribution cavity outer cover plate, the oxidant flow equalizing plate and the oxidant flow equalizing circumferential seam;

the fuel injection assembly comprises a fuel injector, a fuel nozzle, a combustion chamber external fuel pipe and a combustion chamber fuel channel, wherein one end of the combustion chamber fuel channel is communicated with the combustion chamber external fuel pipe, the other end of the combustion chamber fuel channel is connected with the fuel injector, the fuel nozzle is arranged on the fuel injector, and fuel enters the fuel injector through the combustion chamber external fuel pipe and the combustion chamber fuel channel and enters the annular seam combustion chamber through the fuel nozzle.

Furthermore, the oxidant inlet cavity shell part is in a conical structure, and the oxidant inlet is arranged at the central axis position of the oxidant inlet cavity shell.

Furthermore, the oxidant air inlet cavity shell comprises a conical section and a straight cylinder section, the small diameter end of the conical section is an oxidant inlet, the large diameter end of the conical section is connected with one end of the straight cylinder section, and the other end of the straight cylinder section is connected with one end of an oxidant distribution inlet of the circumferential seam combustion chamber.

Further, the number of the fuel pipes connected to the outside of the combustion chamber may be plural, and the oxidant inlet and the fuel pipes connected to the outside of the combustion chamber may control the inflow rate by separate solenoid valves and flow meters.

Further, the number of the oxidant flow equalizing ring seams can be multiple.

Further, the circumferential seam combustion chamber can be a multi-layer circumferential seam combustion chamber which is coaxially sleeved.

Further, the detonation combustor includes a plurality of single channel oxygen supply detonation combustor modules.

Further, the detonation combustor still includes ignition assembly, and ignition assembly includes that the combustion chamber punctures ignition channel and predetonation pipe point firearm, and predetonation pipe point firearm sets up and punctures the ignition channel and communicates to the circumferential weld combustion chamber at the outside of combustion chamber and through the combustion chamber.

Furthermore, the arrangement mode of the single-channel oxygen supply detonation combustion chamber module comprises one or more of coaxial sleeve, linear shape, star shape, circular shape, oval shape and triangular shape.

Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise:

the detonation engine adopting the unique multi-annular-seam combustion chamber structural design enlarges the adjustable range of the thrust, controls the change of the thrust by combining the working states of a plurality of combustion chambers, has a simple and effective control system, and realizes the rapid and accurate adjustment and control of the wide-range thrust, so the maximum thrust-weight ratio can be made larger, and the lower limit of the minimum thrust is smaller; secondly, the inner ring, the outer ring and the adjacent position space are fully utilized, and a combustion chamber is designed along with the appearance of the aircraft, so that the utilization rate of the space is improved; thirdly, the combustion chamber adopts multi-channel fuel supply, which is not affected mutually, stable and safe; the oxidant supply channel of single channel, the channel structure of oxidant is simple, and the ignition of polycyclic combustion chamber is realized to the oxidant supply all the way, and the combustion chamber that does not work still has the oxidant to pass through, provides cooling protection for adjacent combustion chamber, provides another kind of air film cooling's thinking.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used 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 it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a side view of a first embodiment of the present invention;

FIG. 2 isbase:Sub>A cross-sectional view ofbase:Sub>A section of the 2 nd fuel cavity of section A-A of FIG. 1;

FIG. 3 is an axial rear view of the first embodiment of the present invention;

FIG. 4 is a cross-sectional view of section 1/3 of the fuel chamber of section B-B of FIG. 3;

FIG. 5 is an axial rear view of the first embodiment of the present invention;

FIG. 6 is a sectional view of a section of the section C-C oxidant distribution chamber of FIG. 5;

FIG. 7 is a cross-sectional view of the D-D section of the pre-squib ignition section of FIG. 1;

FIG. 8 is a schematic view of an oxidant distribution inlet of a first embodiment of the present invention for a circumferential seam combustor;

FIG. 9 is a perspective view of the first embodiment of the present invention;

FIG. 10 is an axial cross-sectional view of a second embodiment of the present invention;

FIG. 11 is an axial cross-sectional view of a third embodiment of the invention;

fig. 12 is an axial cross-sectional view of a fourth embodiment of the present invention.

Description of the reference numerals: 1. an oxidant inlet chamber housing; 2. the inner circumferential seam combustion chamber is externally connected with a fuel pipe group; 3. the middle circular seam combustion chamber is externally connected with a fuel pipe group; 4. the outer circumferential seam combustion chamber is externally connected with a fuel pipe group; 5. a fuel injector; 6. an oxidant distribution chamber outer cover plate; 7. an oxidant flow equalizing plate; 8. a combustor casing; 9. a combustion chamber first intermediate housing; 10. a combustion chamber second intermediate housing; 11. an inner ring body; 12. an inner circumferential seam combustion chamber; 13. a middle circular seam combustion chamber; 14. an outer circumferential seam combustion chamber; 15. a fuel nozzle; 16. a middle circular seam combustion chamber fuel channel; 17. an oxidant pressure stabilizing cavity; 18. a combustor oxidant distribution inlet; 19. an oxidant inlet; 20. an oxidant flow equalizing circular seam; 21. a pre-booster igniter; 22. the middle circular seam combustion chamber breaks down an ignition channel; 23. the inner circular seam combustion chamber breaks down an ignition channel; 24. the fuel channel of the inner circumferential seam combustion chamber; 25. the outer circumferential seam combustion chamber fuel passage.

Detailed Description

The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.

It is noted that various aspects of the embodiments are described below within the scope of the appended 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 application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number and aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.

It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.

In addition, in the following description, specific details are provided to facilitate 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 combustion chamber of the continuous rotation detonation engine in the prior art has the following defects:

1. the structure is single, the single circular seam is mostly adopted, and the thrust-weight ratio of a single material is low under the condition that a novel light material is not adopted;

2. the single combustion chamber has low space utilization rate, the inner annular space of the annular seam combustion chamber with a certain cross section size is basically solid or purely hollow to reduce weight, the part of the cross section does not generate thrust, and the space is wasted;

3. compared with a multi-annular-seam combustion chamber, the combustion chamber has only one specification, the combustion annular seam space of the combustion chamber cannot be adjusted, cannot be enlarged or reduced, or the quantity of the combustion annular seam space is increased, the coupled ignition and explosion starting are realized, and the improvement of power is not essentially changed;

4. the range of the adjustable thrust is small, the single-ring thrust lifting mode is mainly used for optimizing combustion, improving the mixing effect of an oxidant and fuel and improving the flow, but the cross section of a combustion chamber is certain, so that the adjustable range is quite limited;

5. because variable thrust is needed, a control system of the single-crack combustion chamber is relatively complex, the number of parts is large, the cost is high, the reliability is low, and the design purpose of a knock engine with simple construction is violated;

6. the single combustion chamber is also designed with a single channel for fuel entering, once the fuel in a certain channel fails and stops being supplied, the engine cannot work, the safe supply of the fuel in the multiple channels is often required for the aircraft with special purposes, and the engine can work stably;

7. the single slot combustor regenerative cooling requires additional upgrades to the individual cooling channels, and the multiple slot combustor can provide cooling to adjacent combustors in an inoperative condition, providing an alternative film cooling concept.

Aiming at the problems of low space utilization rate and variable thrust provided by a circular seam detonation engine, the number of circular seams can be increased inwards on the basis of a single circular seam combustion chamber, the maximum size of the combustion chamber of the engine is not changed, the space is fully utilized, and the thrust is controlled by single-ring ignition or multi-ring ignition. Meanwhile, the number of the circular seams can be increased outwards on the basis of the single circular seam combustion chamber, the length size and the minimum radial direction of the combustion chamber of the engine are not changed, the space is fully utilized under the condition that the aircraft is not greatly changed or even changed, and the control of thrust is realized by single-ring ignition or multi-ring ignition. Or the number of the inner and outer axial and radial circular seams is increased simultaneously, so that the wide-area adjustability of the thrust is realized.

The technical solutions provided by the embodiments of the present application are described below with reference to the accompanying drawings.

Fig. 1 to 9 show an embodiment of the present invention.

The present embodiment is a detonation engine having a single oxidant passage, three fuel passages, and having three concentric radially disposed annular crevice combustion chambers.

As shown in FIG. 1, the detonation engine includes an oxidizer supply assembly, a fuel injection assembly, a combustor assembly and an ignition assembly.

The oxidant supply assembly includes: the oxidant inlet cavity comprises an oxidant inlet cavity shell 1, an oxidant pressure stabilizing cavity 17, a circular seam combustion chamber oxidant distribution inlet 18, an oxidant inlet 19, an oxidant flow equalizing plate 7 and an oxidant flow equalizing circular seam 20. The oxidant pressure stabilizing cavity 17 is a transverse conical structure, a unique oxidant inlet 19 is positioned on the central axis of the oxidant inlet cavity shell 1, and the oxidant inlet 19 is arranged in the center, so that oxidant can flow into each combustion chamber more uniformly. The oxidant inlet cavity shell 1 comprises a conical section and a straight cylinder section, wherein the small-diameter end of the conical section is provided with an oxidant inlet 19, the large-diameter end of the conical section is connected with one end of the straight cylinder section, and the other end of the straight cylinder section is connected with one end of an oxidant distribution inlet 18 of the circumferential seam combustion chamber. A plurality of oxidant flow equalizing circular seams 20 are arranged between the oxidant flow equalizing plate 7 and the circular seam combustion, and the oxidant enters the circular seam combustion chamber through the oxidant distribution inlet 18 of the circular seam combustion chamber, the oxidant flow equalizing plate 7 and the oxidant flow equalizing circular seams 20.

The fuel injector assembly comprises: a mid-annular seam combustor fuel passage 16, fuel nozzles 15, fuel injectors 5, combustor external fuel pipes, an outer annular seam combustor fuel passage 25, and an inner annular seam combustor fuel passage 24. The external fuel connection pipe of the combustion chamber comprises an external fuel pipe group 4 of an outer annular seam combustion chamber, an external fuel pipe group 3 of a middle annular seam combustion chamber and an external fuel pipe group 2 of an inner annular seam combustion chamber. The outer fuel tube group 3 of the inner annular seam combustion chamber and the outer fuel tube group 4 of the outer annular seam combustion chamber respectively comprise four outer fuel tubes; the oxidant flow equalization plate 7 is fed around the nozzle annulus around each fuel nozzle 15.

The combustor assembly includes: fuel nozzle 15, combustor casing 8, combustor first intermediate casing 9, combustor second intermediate casing 10, inner ring 11, circumferential seam combustor and oxidizer distribution chamber outer cover plate 6. The circular seam combustion chamber comprises an inner circular seam combustion chamber 12, a middle circular seam combustion chamber 13 and an outer circular seam combustion chamber 14. The oxidizer supply assembly is connected to the combustor assembly by an oxidizer distribution chamber outer cover plate 6. The combustion chamber component is an inner ring body 11, a second middle shell 10, a first middle shell 9 and a combustion chamber shell 8 which are coaxial and are sleeved from inside to outside in sequence. The inner circumferential seam combustion chamber 12 is an annular cavity formed by the second middle shell 10 and the inner ring 11 of the combustion chamber in a surrounding manner. The middle annular seam combustion chamber 13 is an annular cavity formed by surrounding the first middle shell 9 and the second middle shell 10 of the combustion chamber. The outer annular seam combustion chamber 14 is an annular cavity formed by the second middle shell 10 of the combustion chamber and the combustion chamber shell 8 in a surrounding mode.

The ignition assembly includes: the combustion chamber breaks down the ignition channel and the pre-squib igniter 21. The combustion chamber breakdown ignition channel comprises a middle annular seam combustion chamber breakdown ignition channel 22 and an inner annular seam combustion chamber breakdown ignition channel 23. The pre-explosion pipe igniter 21 is arranged outside the whole combustion chamber, the pre-explosion pipe igniter 21 is communicated to the outer annular seam combustion chamber 14 and is respectively communicated to the middle annular seam combustion chamber 13 and the inner annular seam combustion chamber 12 through a middle annular seam combustion chamber breakdown ignition channel 22 and an inner annular seam combustion chamber breakdown ignition channel 23. In this case, the pre-squib igniter 21 can achieve ignition with a small amount of energy.

The working principle of the embodiment is as follows:

the oxidant is connected into an oxidant pressure stabilizing cavity 17 formed by the oxidant inlet cavity shell 1 through an external oxidant filling cavity connecting device, a single electromagnetic valve, a flowmeter and an oxidant inlet 19, and flows into the inner annular seam combustion chamber 12, the middle annular seam combustion chamber 13 and the outer annular seam combustion chamber 14 through an oxidant distribution inlet 18, an oxidant flow equalizing plate 7 and an oxidant flow equalizing annular seam 20 of the combustion chamber shown in figure 6.

The fuel is controlled to be connected into the fuel pipe outside the combustion chamber through a fuel electromagnetic valve and a fuel flow meter by a plurality of independent external fuel connecting devices and is connected with the fuel pipe outside the combustion chamber, and the fuel pipe outside the combustion chamber comprises an external fuel pipe group 4 of an outer annular seam combustion chamber, an external fuel pipe group 3 of a middle annular seam combustion chamber and an external fuel pipe group 2 of an inner annular seam combustion chamber. Fuel is injected through the fuel injectors 5 to the outer annular slot combustion chamber 14, the middle annular slot combustion chamber 13, and the inner annular slot combustion chamber 12. The fuel mixes with the oxidizer dispensed from the combustor oxidizer distribution inlet 18 to form a well-mixed detonatable mixture and ignition is achieved by the pre-squib igniter 21. Ignition energy is transmitted to the middle annular gap combustion chamber 13 through the middle annular gap combustion chamber breakdown ignition channel 22, and is transmitted to the inner annular gap combustion chamber 12 through the inner annular gap combustion chamber breakdown ignition channel 23, and ignition of a plurality of combustion chambers through one igniter is achieved. The fuel is high-risk combustible, the safety of the engine can be enhanced by the multi-channel design, and the engine can still operate conditionally as long as all the channels are not broken down.

According to different application scenes, the principle for realizing thrust change is as follows:

1. the work of each combustion chamber is controlled by controlling independent fuel supply, so that the wide range of the thrust is adjustable.

The fuel tube group 4 externally connected with the outer annular seam combustion chamber, the fuel tube group 3 externally connected with the middle annular seam combustion chamber and the fuel tube group 2 externally connected with the inner annular seam combustion chamber are connected and disconnected, so that the separate work or the pairwise combined work or the simultaneous full-load work of each annular seam combustion chamber (the outer annular seam combustion chamber 14, the middle annular seam combustion chamber 13 and the inner annular seam combustion chamber 12) is realized, the control from the independent ignition to the full-load ignition combustion of different annular seam combustion chambers is realized, the thrust can be adjusted in wide range, under the condition that a certain combustion chamber is not ignited, an oxidant can flow through the annular seam combustion chamber, a part of heat is taken away, and the cooling protection of the working combustion chamber is realized. The oxidant single channel sets up, from control and structural simpler, as long as control a passageway, can adapt to the ignition combination of multiple combustion chamber, and partial heat can be taken away to the passageway that does not ignite, cools off the protection to adjacent combustion chamber wall.

2. The compact arrangement of the combustion chamber can maximize the thrust in a limited space.

In the aspect of spatial arrangement, because compact arrangement is added, inward arrangement can be realized for the combustion chamber with the smaller section diameter and the circular seam, and the lower limit of thrust is improved; outwards, the outer wall surface of the outer ring can be used as an inner ring body in a conventional design, the number of combustion chambers is increased, the arrangement can be more compact, and the upper limit of thrust can be larger than that of a single ring under the condition that the cross section is fixed.

After the combustion working state is finished, the fuel supply is stopped firstly, the inert gas nozzle electromagnetic valve externally connected with the fuel pipeline is electrified to start working, the fuel cavity is purged by gas, redundant fuel is swept, the wall surface of the combustion chamber is cooled for a short time, and a complete working cycle is finished.

The multi-annular-seam detonation combustion chamber of the first embodiment of the invention can be coaxially arranged inwards on the existing engine, or the existing outer wall is used as a part of a newly-added combustion chamber, so that the arrangement is more compact; due to the design of the independent multi-fuel channel, the control is simple, and the safety and the obstacle avoidance performance are greatly improved; the single-channel oxidant channel is designed, the structure is simple, the control is simple and convenient, one oxidant channel is suitable for the combined ignition of a plurality of combustion chambers, and the oxidant still flows through the combustion chambers which do not work to cool the wall surfaces of the adjacent combustion chambers; the circular seam combustion chamber ignition mode adopts the igniter of the form of a predetonation tube, any combustion chamber can be ignited independently, a plurality of ignition devices do not need to be designed independently, the number of parts is reduced, and the assembly cost is reduced.

The working principle of the other embodiments of the present invention is the same as that of the first embodiment.

Fig. 9 and fig. 10 show a second embodiment of the present invention, in which the detonation engine of this embodiment has five annular slit combustion chambers, and the annular slit combustion chambers are coaxially arranged in a sleeving manner. The thrust force can be larger by increasing the number of the annular slit combustion chambers more than in the first embodiment.

Fig. 11 shows a third embodiment of the present invention, in which the knocking engine is a knocking engine having a plurality of annular seam combustion chambers of the same size and arranged in a straight line. The straight distribution enables a larger number of combustion chambers to be arranged in the fixed space.

Fig. 12 shows a fourth embodiment of the present invention, in which the knocking engine is a knocking engine having a plurality of annular slit combustion chambers of the same size and arranged in a star shape.

In other implementations, the annular seam combustion chambers of the detonation engine can be a plurality of asymmetric annular seam combustion chambers with different sizes according to the actual conditions of engines of different models, and the distribution mode of the annular seam combustion chambers of the detonation engine can also be circular, elliptical, triangular and other distribution modes.

The detonation engine with the unique multi-annular-seam combustion chamber structural design can enlarge the range of adjustable thrust, can control the change of the thrust by combining the working states of a plurality of combustion chambers, has a simple and effective control system, and realizes the rapid and accurate adjustment and control of the wide-range thrust, so the maximum thrust-weight ratio can be made larger, and the lower limit of the minimum thrust can be smaller; secondly, the inner ring, the outer ring and the adjacent space are fully utilized, and the annular seam combustion chamber is designed according to the shape of the aircraft, so that the utilization rate of the space is improved; the multi-annular-seam combustion chamber is supplied by multiple channels of fuel, so that the multi-annular-seam combustion chamber is not influenced mutually, stable and safe; the multi-channel oxidant supply channel has more accurate control of the oxidant, the multiple oxidants are supplied to correspond to the ignition of the multi-ring combustion chambers, and the oxidant and the fuel are supplied to each combustion chamber corresponding to the single channel; the equivalent ratio is controlled by reducing the carrying of the oxidant and accurately controlling the supply, so that the real-time accurate regulation and control of the thrust is realized; when the combustor is not in operation, the oxidant can be continuously supplied in a controlled manner, and another idea of combustor gas film cooling is provided.

The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are 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 simple, and for the relevant points, reference may be made to the partial description of the system embodiments.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A single channel oxygen supply detonation combustor module, comprising:

the combustor assembly comprises a circumferential seam combustor, an inner ring body (11) and a combustor shell (8), wherein the inner ring body and the combustor shell are coaxially sleeved from inside to outside in sequence, and the circumferential seam combustor is an annular cavity formed by the combustor shell (8) and the inner ring body (11) in a surrounding mode;

the oxidant supply assembly comprises an oxidant inlet (19), an oxidant inlet cavity shell (1), an oxidant pressure stabilizing cavity (17), an oxidant distribution inlet (18) of a circumferential seam combustion chamber, an oxidant flow equalizing plate (7) and an oxidant distribution cavity outer cover plate (6), wherein the oxidant inlet (19) is arranged on the outer wall of the oxidant inlet cavity shell (1) in a penetrating manner, the oxidant pressure stabilizing cavity (17) is a cavity inside the oxidant inlet cavity shell (1), one end of the circumferential seam combustion chamber oxidant distribution inlet (18) is communicated with the oxidant pressure stabilizing cavity (17), the other end of the circumferential seam combustion chamber oxidant distribution inlet (18) is communicated with the oxidant distribution cavity outer cover plate (6), the oxidant distribution cavity outer cover plate (6) is communicated with the oxidant flow equalizing plate (7), an oxidant flow equalizing circumferential seam (20) is arranged between the oxidant flow equalizing plate (7) and the circumferential seam combustion, and the oxidant pressure stabilizing cavity (17) is correspondingly communicated with the circumferential seam combustion chamber through the circumferential seam oxidant distribution inlet (18), the oxidant distribution cavity outer cover plate (6), the oxidant flow equalizing plate (7) and the oxidant circumferential seam (20);

the fuel injection assembly comprises a fuel injector (5), a fuel nozzle (15), a combustion chamber external fuel pipe and a combustion chamber fuel channel, wherein one end of the combustion chamber fuel channel is communicated with the combustion chamber external fuel pipe, the other end of the combustion chamber fuel channel is connected with the fuel injector (5), the fuel nozzle (15) is arranged on the fuel injector (5), and fuel enters the fuel injector (5) through the combustion chamber external fuel pipe and the combustion chamber fuel channel and enters the annular seam combustion chamber through the fuel nozzle (15).

2. The single channel oxygen supply detonation combustor module of claim 1, characterized in that the oxidant inlet chamber housing (1) is partially conical in configuration, and the oxidant inlet (19) is disposed at a central axis of the oxidant inlet chamber housing (1).

3. The single channel oxygen supply detonation combustor module of claim 1, characterized in that the oxidant inlet chamber housing (1) includes a conical section and a straight section, the small diameter end of the conical section is an oxidant inlet (19), the large diameter end of the conical section is connected with one end of the straight section, and the other end of the straight section is connected with one end of a circular seam combustor oxidant distribution inlet (18).

4. The single pass oxygen supply detonation combustor module of claim 1, wherein the combustor external fuel line may be multiple, and wherein the oxidant inlet (19) and the combustor external fuel line may each be controlled by separate solenoid valves and flow meters for inflow.

5. The single channel oxygen supply detonation combustor module of claim 1, wherein there may be a plurality of oxidant flow equalizing circumferential slots.

6. The single channel oxygen supply detonation combustor module of claim 1, wherein the circumferential seam combustor may be a coaxially nested multi-layer circumferential seam combustor.

7. A detonation combustor comprising a single channel oxygen supply detonation combustor module, wherein the single channel oxygen supply detonation combustor module is the single channel oxygen supply detonation combustor module of any of claims 1-6.

8. The detonation combustor of claim 7, wherein the detonation combustor comprises a plurality of the single channel oxygen supply detonation combustor modules.

9. The detonation combustor of claim 7, further comprising an ignition assembly including a combustor breakdown ignition channel and a pre-squib igniter (21), the pre-squib igniter (21) disposed outside of the combustor and communicating to the annular seam combustor through the combustor breakdown ignition channel.

10. The detonation combustor of claim 8, wherein the arrangement of the single-channel oxygen supply detonation combustor modules comprises one or a combination of several of a coaxial sleeve, a straight line shape, a star shape, a circular shape, an oval shape and a triangular shape.