阅读说明：本技术 能实现切向不稳定燃烧与连续旋转爆震的发动机及方法 (Engine and method capable of realizing tangential unstable combustion and continuous rotation detonation ) 是由 林伟 范良忠 罗修棋 谢远 仝毅恒 王家森 晏成龙 郭康康 舒晨 于 2021-04-16 设计创作，主要内容包括：本发明公开了一种能实现切向不稳定燃烧与连续旋转爆震的发动机及方法,包括分区喷注系统、燃烧室和拉瓦尔喷管三大部分。推进剂分为燃料、氧化剂两路来流,其中每一路按特定质量比再分为两股。其中,两股燃料分别进入外燃料集气腔和内燃料集气腔,两股氧化剂进入外氧化剂集气腔和内氧化剂集气腔。内燃料集气腔与内氧化剂集气腔组成液体火箭发动机同轴直流式喷嘴喷注模式,外燃料集气腔与外氧化剂集气腔组成旋转爆震环缝式喷注模式。圆柱构型的燃烧室壁面有电火花点火器和切向热射流点火器,与两种喷注方式配合可分别激发液体火箭发动机工作模态、旋转爆震模态及复合模态。(The invention discloses an engine and a method capable of realizing tangential unstable combustion and continuous rotation detonation. The propellant is divided into two incoming flows of fuel and oxidizer, wherein each incoming flow is divided into two flows according to a specific mass ratio. Wherein, two streams of fuel enter an outer fuel gas-collecting cavity and an inner fuel gas-collecting cavity respectively, and two streams of oxidant enter an outer oxidant gas-collecting cavity and an inner oxidant gas-collecting cavity. The inner fuel gas-collecting cavity and the inner oxidant gas-collecting cavity form a coaxial straight-flow nozzle injection mode of the liquid rocket engine, and the outer fuel gas-collecting cavity and the outer oxidant gas-collecting cavity form a rotary detonation annular seam injection mode. The wall surface of the combustion chamber with the cylindrical structure is provided with an electric spark igniter and a tangential hot jet igniter, and the electric spark igniter and the tangential hot jet igniter are matched with two injection modes to respectively excite a working mode, a rotary detonation mode and a composite mode of the liquid rocket engine.)

1. An engine capable of realizing tangential unstable combustion and continuous rotation knocking is characterized in that: the burner comprises an end cover, an injection assembly and a combustion chamber which are coaxially arranged from front to back in sequence;

the combustion chamber comprises a combustion chamber shell, and an electric spark igniter and a tangential hot jet igniter which are arranged on the combustion chamber shell;

the injection assembly comprises an injection panel and a plurality of fuel nozzles uniformly arranged in the center of the injection panel;

an inner fuel channel is arranged in the center of each fuel nozzle;

the injection panel comprises a clapboard, a lining, an outer lining and a sealing ring sleeve;

the inner liner is a barrel body with an outer end opening, and the bottom surface of the barrel body is formed into an injection surface facing the combustion chamber; the jetting surface is provided with jet holes with the number equal to that of the fuel nozzles, the jetting end of each fuel nozzle extends into the jet holes, the outer diameter of the jetting end of each fuel nozzle is smaller than the inner diameter of the corresponding jet hole, and an inner oxidant channel is formed between the outer wall surface of the jetting end of each fuel nozzle and the inner wall surface of the corresponding jet hole;

the end cover sealing cover is arranged at an opening at the outer end of the inner liner and forms an inner propellant sealing cavity with the inner liner;

the partition plate divides the inner propellant sealed cavity into an inner fuel gas-collecting cavity and an inner oxidant gas-collecting cavity; wherein the inner fuel gas collecting cavity is communicated with each inner fuel channel; the inner oxidant gas-collecting cavity is communicated with each inner oxidant channel;

the outer liner is coaxially sleeved on the periphery of the inner liner, one end of the outer liner is fixedly connected with the inner liner or the end cover in a sealing manner, and the other end of the outer liner is integrally arranged with the combustion chamber shell; an outer oxidant channel in a seam shape is formed between the outer lining and the inner lining;

the outer wall surface of the outer lining is provided with an annular groove, and the sealing ring sleeve is hermetically covered on the periphery of the sealing groove to form an outer fuel gas-collecting cavity;

the outer liner is provided with a plurality of inclined outer fuel channels along the circumferential direction, and each outer fuel channel is communicated with the outer fuel gas-collecting cavity and the combustion chamber.

2. The engine capable of achieving tangentially unstable combustion with continuous rotational detonation of claim 1, characterized in that: the number of fuel nozzles is seven, each fuel nozzle is a coaxial shear nozzle, one of which is installed in the exact center of the injection panel, called the center fuel nozzle, and the remaining six fuel nozzles are evenly distributed on the same circumferential line on the periphery of the center fuel nozzle.

3. The engine capable of achieving tangentially unstable combustion with continuous rotational detonation of claim 1, characterized in that: the outer fuel gas-collecting cavity and the inner fuel gas-collecting cavity are both connected with a high-pressure fuel gas bottle through a fuel flow distributor; the outer oxidant passage and the inner oxidant gas-collecting cavity are both connected with a high-pressure oxidant gas cylinder through an oxidant flow distributor.

4. The engine capable of achieving tangentially unstable combustion with continuous rotational detonation of claim 1, characterized in that: the number of outer fuel passages is 90.

5. The engine capable of achieving tangentially unstable combustion with continuous rotational detonation of claim 1, characterized in that: an observation window is arranged on the combustion chamber shell.

6. The engine capable of achieving tangentially unstable combustion with continuous rotational detonation of claim 1, characterized in that: the tail end of the combustion chamber is detachably connected with a Laval nozzle.

7. A method for realizing tangential unstable combustion and continuous rotation detonation is characterized by comprising the following steps: on the premise that the total fuel flow and the total oxidant flow are not changed, the fuel flow entering the outer fuel gas collecting cavity and the inner fuel gas collecting cavity is adjusted through the fuel flow distributor, and the oxidant flow entering the outer oxidant channel and the inner oxidant gas collecting cavity is adjusted through the oxidant flow distributor, so that an independent tangential unstable combustion mode, an independent continuous rotation detonation and a composite mode can be realized.

8. The method of claim 7 for achieving tangentially unstable combustion with continuous rotational detonation, characterized in that: the method for realizing the single tangential unstable combustion mode comprises the following steps: all the fuel with flow rate enters the inner fuel gas-collecting cavity by controlling the fuel flow rate distributor and enters the combustion chamber through the coaxial shear type nozzle; meanwhile, all the oxidant at the flow rate enters the combustion chamber through the inner oxidant channel by controlling the oxidant flow rate distributor; the fuel and oxidant entering the combustion chamber are mixed and ignited by matching with an electric spark igniter, so that a tangential unstable combustion mode is realized.

9. The method of claim 7 for achieving tangentially unstable combustion with continuous rotational detonation, characterized in that: the method for realizing the single continuous rotation knocking mode comprises the following steps: all the flow rate of fuel enters the outer fuel gas-collecting cavity by controlling the fuel flow rate distributor and enters the combustion chamber through a plurality of outer fuel channels, and all the flow rate of oxidant enters the combustion chamber through the outer oxidant channels by controlling the oxidant flow rate distributor; the fuel and oxidant entering the combustion chamber are mixed and cooperate with the tangential hot jet igniter to ignite, thereby realizing a continuous rotation detonation mode.

10. The method of claim 7 for achieving tangentially unstable combustion with continuous rotational detonation, characterized in that: the method for realizing the composite mode comprises the following steps: the mass flow ratio of the fuel in the outer fuel gas-collecting cavity and the inner fuel gas-collecting cavity is controlled through a fuel flow distributor, so that part of the fuel with flow enters the inner fuel gas-collecting cavity, and the other part of the fuel with flow enters the outer fuel gas-collecting cavity;

controlling the mass flow ratio of the oxidant in the outer oxidant passage and the inner oxidant gas-collecting cavity through the oxidant flow distributor, so that part of the oxidant with flow enters the inner fuel gas-collecting cavity and the inner oxidant channel, and the other part of the oxidant with flow enters the outer oxidant passage;

the fuel entering the inner fuel gas-collecting cavity passes through the coaxial shear type nozzle, is mixed with the oxidant sprayed from the inner oxidant channel, enters the combustion chamber, and is matched with the electric spark igniter for ignition, so that a tangential unstable combustion mode is realized;

the fuel entering the outer fuel gas-collecting cavity passes through the outer fuel channel, is mixed with the oxidant sprayed out of the outer oxidant channel, enters the combustion chamber, and is ignited by matching with the tangential thermal jet igniter, so that a continuous rotation detonation mode is realized;

the mass flow ratio of the corresponding propellant is adjusted by adjusting the fuel flow distributor and the oxidant flow distributor, so that the relation and the transformation rule of tangential unstable combustion and continuous rotation detonation can be continuously observed, and the unstable excitation mechanism of the tangential combustion of the liquid rocket engine is explained by utilizing the rotation detonation theory.

Technical Field

The invention relates to the technical field of space propulsion, in particular to an engine and a method capable of realizing tangential unstable combustion and continuous rotation detonation.

Background

Tangential combustion instabilities in liquid rocket engines, once they occur, are extremely destructive. Therefore, the limitation of the instability of tangential combustion is always one of the key technologies for developing a high-thrust rocket engine.

The research on the unstable mechanism of combustion is highly regarded by researchers in various countries. Still, scientists have not found a reliable theoretical design guide for more than sixty years, and the suppression of the tangential firing instability still depends on empirical methods such as trial and error studies for installing diaphragms and acoustic cavities of various structures, which however requires a large investment and an extremely long development period.

In recent years, attention is paid to the relation between unstable tangential combustion and continuous rotation knocking, parameters such as propagation forms, frequency characteristics and the like of the tangential combustion and the continuous rotation knocking are found to be very close, the mechanisms of the tangential combustion and the continuous rotation knocking are considered to have certain similarity, and meanwhile, the tangential combustion and the continuous rotation knocking are different in implementation means such as structural configurations, injection modes and ignition modes. However, the existing experimental equipment for studying the relationship between the unstable tangential combustion and the continuous rotation knocking has the following defects and needs to be improved:

1. at present, the tangential combustion instability is mainly researched by matching a configuration of a liquid rocket engine with a nozzle, the continuous rotation detonation is researched by matching an annular combustion chamber with circumferential seam injection, the test processes are independent, and although the results are compared and analyzed finally, the relevance of the two is still blurred to the great extent.

2. Some researchers integrate the two modes into one test device, but the flow ratio of the injection of the two modes cannot be continuously adjusted in the test process, so that the process of mutual transformation of the two modes cannot be observed, and the critical condition of the transformation of the two modes cannot be obtained.

Disclosure of Invention

The invention aims to solve the technical problem of the prior art and provides an engine and a method capable of realizing tangential unstable combustion and continuous rotation detonation, wherein the engine and the method capable of realizing tangential unstable combustion and continuous rotation detonation are provided with four gas collecting cavities to support two sets of independent injection modes, namely a nozzle and a circular seam, and the flow distribution is continuously adjustable. When all the flow enters a combustion chamber through a coaxial shear nozzle by controlling a flow distributor in a supply pipeline, circumferential seam injection does not work, and is matched with electric sparks for isobaric ignition, namely a liquid rocket engine mode; when all the flow enters the combustion chamber through the annular seam, the nozzle does not work and is matched with tangential thermal jet for ignition, and the mode is an empty barrel rotation detonation mode at the moment; when the nozzle and the circular seam work simultaneously, the compound mode is adopted, the relation and the transformation rule of the tangential instability and the rotary detonation of the liquid rocket engine can be continuously observed by adjusting the mass flow ratio of the two injection modes, and then the excitation mechanism of the tangential combustion instability of the liquid rocket engine is explained by utilizing the rotary detonation theory.

In order to solve the technical problems, the invention adopts the technical scheme that:

an engine capable of realizing tangential unstable combustion and continuous rotation detonation comprises an end cover, an injection assembly and a combustion chamber which are coaxially arranged from front to back in sequence.

The combustor includes a combustor housing, and an electric spark igniter and a tangential thermal jet igniter mounted on the combustor housing.

The jetting assembly includes a jetting panel and a number of fuel nozzles uniformly mounted in the center of the jetting panel.

An inner fuel passage is provided in the center of each fuel nozzle.

The injection panel comprises a partition plate, an inner liner, an outer liner and a sealing ring sleeve.

The inner lining is a barrel body with an outer end opening, and the bottom surface of the barrel body is formed into an injection surface facing the combustion chamber. The jetting surface is provided with jet holes with the number equal to that of the fuel nozzles, the jetting end of each fuel nozzle extends into the jet holes, the outer diameter of the jetting end of each fuel nozzle is smaller than the inner diameter of the corresponding jet hole, and an inner oxidant channel is formed between the outer wall surface of the jetting end of each fuel nozzle and the inner wall surface of the corresponding jet hole.

The end cover sealing cover is arranged at the opening of the outer end of the inner liner and forms an inner propellant sealing cavity together with the inner liner.

The partition plate divides the inner propellant sealed cavity into an inner fuel gas-collecting cavity and an inner oxidant gas-collecting cavity. Wherein, the inner fuel gas collecting cavity is communicated with each inner fuel channel. The inner oxidant gas-collecting cavity is communicated with each inner oxidant channel.

The outer lining is coaxially sleeved on the periphery of the inner lining, one end of the outer lining is fixedly connected with the inner lining or the end cover in a sealing mode, and the other end of the outer lining and the combustion chamber shell are integrally arranged. An outer oxidant channel in a seam shape is formed between the outer lining and the inner lining.

The outer wall surface of the outer lining is provided with an annular groove, and the sealing ring sleeve is covered on the periphery of the sealing groove in a sealing manner to form an outer fuel gas-collecting cavity.

The outer liner is provided with a plurality of inclined outer fuel channels along the circumferential direction, and each outer fuel channel is communicated with the outer fuel gas-collecting cavity and the combustion chamber.

The number of fuel nozzles is seven, each fuel nozzle is a coaxial shear nozzle, one of which is installed in the exact center of the injection panel, called the center fuel nozzle, and the remaining six fuel nozzles are evenly distributed on the same circumferential line on the periphery of the center fuel nozzle.

The outer fuel gas-collecting cavity and the inner fuel gas-collecting cavity are both connected with a high-pressure fuel gas bottle through a fuel flow distributor. The outer oxidant passage and the inner oxidant gas-collecting cavity are both connected with a high-pressure oxidant gas cylinder through an oxidant flow distributor.

The number of outer fuel passages is 90.

An observation window is arranged on the combustion chamber shell.

The tail end of the combustion chamber is detachably connected with a Laval nozzle.

On the premise of keeping the total fuel flow and the total oxidant flow unchanged, the fuel flow entering an outer fuel gas collecting cavity and an inner fuel gas collecting cavity is adjusted through a fuel flow distributor, and the oxidant flow entering an outer oxidant channel and an inner oxidant gas collecting cavity is adjusted through an oxidant flow distributor, so that an independent tangential unstable combustion mode, an independent continuous rotary detonation mode and a composite mode can be realized.

The method for realizing the single tangential unstable combustion mode comprises the following steps: all the fuel flow enters the inner fuel gas collecting cavity by controlling the fuel flow distributor and enters the combustion chamber through the coaxial shear type nozzle. Meanwhile, the oxidant flow distributor is controlled to ensure that all the oxidant flows enter the inner oxidant gas-collecting cavity and enter the combustion chamber through the inner oxidant channel. The fuel and oxidant entering the combustion chamber are mixed and ignited by matching with an electric spark igniter, so that a tangential unstable combustion mode is realized.

The method for realizing the single continuous rotation knocking mode comprises the following steps: all the flow rate of fuel enters the outer fuel gas-collecting cavity by controlling the fuel flow rate distributor and enters the combustion chamber through a plurality of outer fuel channels, and all the flow rate of oxidant enters the combustion chamber through the outer oxidant channels by controlling the oxidant flow rate distributor. The fuel and oxidant entering the combustion chamber are mixed and cooperate with the tangential hot jet igniter to ignite, thereby realizing a continuous rotation detonation mode.

The method for realizing the composite mode comprises the following steps: the mass flow ratio of the fuel in the outer fuel gas-collecting cavity and the inner fuel gas-collecting cavity is controlled by the fuel flow distributor, so that part of the fuel enters the inner fuel gas-collecting cavity, and the other part of the fuel enters the outer fuel gas-collecting cavity.

The mass flow ratio of the oxidant in the outer oxidant gas-collecting cavity and the inner oxidant gas-collecting cavity is controlled by the oxidant flow distributor, so that part of the oxidant flows into the inner fuel gas-collecting cavity and the inner oxidant channel, and the other part of the oxidant flows into the outer oxidant channel.

The fuel entering the inner fuel gas-collecting cavity passes through the coaxial shear type nozzle, is mixed with the oxidant sprayed from the inner oxidant channel, enters the combustion chamber, and is matched with the electric spark igniter to ignite, so that the tangential unstable combustion mode is realized.

The fuel entering the outer fuel gas-collecting cavity passes through the outer fuel channel, is mixed with the oxidant sprayed from the outer oxidant channel, enters the combustion chamber, and is ignited by matching with the tangential thermal jet igniter, so that the continuous rotation detonation mode is realized.

The mass flow ratio of the corresponding propellant is adjusted by adjusting the fuel flow distributor and the oxidant flow distributor, so that the relation and the transformation rule of tangential unstable combustion and continuous rotation detonation can be continuously observed, and the unstable excitation mechanism of the tangential combustion of the liquid rocket engine is explained by utilizing the rotation detonation theory.

The invention has the following beneficial effects:

1. the invention combines the isobaric combustion and the continuous rotation detonation of the liquid rocket engine, improves the combustion efficiency compared with the traditional liquid rocket engine, and provides feasible reference for improving the performance of the liquid rocket engine.

2. The invention can simultaneously realize the tangential combustion unstable mode and the rotary detonation mode of the liquid rocket engine and the combined mode of the tangential combustion unstable mode and the rotary detonation mode in one engine, and provides a realization means for researching the relation between the tangential combustion instability and the rotary detonation.

3. The accurately controllable partitioned injection system can realize continuous conversion of various modes in a primary ignition test, and conditions are created for continuously observing a conversion boundary between unstable tangential combustion and rotary detonation.

4. The detachable tail nozzle facilitates the research of the response of various combustion modes to Laval nozzles with different contraction ratios.

Drawings

Fig. 1 shows a schematic diagram of an engine capable of achieving tangential unstable combustion and continuous rotational knocking according to the present invention.

Fig. 2 shows an enlarged partial view of the circular seam injection at i in fig. 1.

FIG. 3 shows an enlarged partial view of the nozzle injection outlet at II in FIG. 1.

FIG. 4 shows a schematic view of the arrangement of several fuel nozzles on the injector panel.

Among them are:

10. an end cap;

21. a partition plate; 211. a nozzle mounting hole;

22. a liner; 221. spraying a hole;

23. an outer liner; 231. an outer oxidant passage; 232. an outer oxidant gas collection chamber; 233. an outer fuel passage; 234. an outer fuel gas-collecting chamber; 235. an outer propellant mixing chamber;

24. sealing the ring sleeve;

25. a fuel nozzle; 251. an inner fuel passage; 252. an inner fuel gas collection chamber; 253. an inner oxidant passage; 254. an inner oxidant gas collection chamber; 255. an inner propellant mixing chamber;

30. a combustion chamber; 31. a combustion chamber housing; 32. an electric spark igniter; 33. a tangential thermal jet igniter; 34. an observation window;

40. a laval nozzle.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.

In the description of the present invention, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.

As shown in fig. 1, 2 and 3, an engine capable of realizing tangential unstable combustion and continuous rotation detonation comprises an end cover 10, an injection assembly, a combustion chamber 30 and a laval nozzle 40 which are coaxially arranged from front to back.

The Laval spray pipe is preferably connected with the tail of the combustion chamber through a bolt, and is convenient to detach and replace, so that the influence of different shrinkage ratios on various working conditions of the engine can be researched.

The combustion chamber comprises a combustion chamber housing 31, and an electric spark igniter 32, a tangential hot jet igniter 33 and a viewing window 34 mounted on the combustion chamber housing.

The observation window can be used for various optical devices to collect data; the tangential thermal jet igniter is responsible for detonation of a continuous rotation detonation mode; the electric spark igniter is used for isobaric combustion ignition of the liquid rocket engine. The electric spark igniter and the tangential hot jet igniter are arranged at the positions which are the same distance from the end face but different phases, and the two ignition modes are flexibly used by matching with different jetting conditions.

The injector assembly comprises an injector panel and a number of fuel nozzles 25 uniformly mounted in the center of the injector panel. In this embodiment, the fuel nozzles are preferably seven, and as shown in fig. 4, each fuel nozzle is a coaxial shear nozzle, one of which is mounted at the very center of the injection panel, referred to as the center fuel nozzle, and the remaining six fuel nozzles are all distributed on the same circumferential line around the periphery of the center fuel nozzle.

An inner fuel passage 251 is provided in the center of each fuel nozzle.

The injection panel comprises a baffle 21, an inner liner 22, an outer liner 23 and a sealing collar 24.

The inner lining is a barrel body with an outer end opening, and the bottom surface of the barrel body is formed into an injection surface facing the combustion chamber.

The injection surface is provided with injection holes 221 with the same number as the fuel nozzles, the injection end of each fuel nozzle extends into the injection holes, the outer diameter of the injection end of each fuel nozzle is smaller than the inner diameter of the corresponding injection hole, and an inner oxidant channel 253 is formed between the outer wall surface of the injection end of each fuel nozzle and the inner wall surface of the corresponding injection hole. Further, the nozzle hole at the front end of the spouting end of each fuel nozzle is formed as an inner propellant mixing chamber 255.

The outer wall surface of the outer end opening end of the inner liner is preferably integrally provided with a flange, and the end cover sealing cover is arranged on the flange at the outer end opening end of the inner liner and forms an inner propellant sealing cavity with the inner liner.

The divider separates the inner propellant containment chamber into an inner fuel plenum 252 and an inner oxidizer plenum 254. Wherein, the inner fuel gas collecting cavity is communicated with each inner fuel channel. The inner oxidant gas-collecting cavity is communicated with each inner oxidant channel.

The partition plate is provided with nozzle mounting holes 211 with the same number of fuel nozzles for sealing and fixing the tail ends of the fuel nozzles.

The outer lining is coaxially sleeved on the periphery of the inner lining, one end of the outer lining is fixedly connected with the inner lining or the end cover in a sealing mode, and the other end of the outer lining and the combustion chamber shell are integrally arranged. An outer oxidant passage 231 in the shape of a slit is formed between the outer liner and the inner liner.

In this embodiment, the outer liner preferably includes a large annular cylinder and a small annular cylinder, which are integrally formed, and the inner diameter of the large annular cylinder is larger than that of the small annular cylinder, so that a seam-shaped outer oxidant gas collecting chamber is formed between the large annular cylinder and the inner liner, and a seam-shaped outer oxidant passage 231 is formed between the small annular cylinder and the inner liner.

The outer wall surface of the outer lining is provided with an annular groove, and the sealing ring sleeve is covered on the periphery of the sealing groove in a sealing manner to form an outer fuel gas-collecting cavity 234.

A plurality of outer fuel channels 233, preferably 90, are circumferentially distributed on the outer liner; each outer fuel channel is communicated with the outer fuel gas-collecting cavity and the combustion chamber.

The outer fuel gas-collecting cavity and the inner fuel gas-collecting cavity are both connected with a high-pressure fuel gas bottle through a fuel flow distributor. The outer oxidant passage and the inner oxidant gas-collecting cavity are both connected with a high-pressure oxidant gas cylinder through an oxidant flow distributor.

On the premise of keeping the total fuel flow and the total oxidant flow unchanged, the fuel flow entering an outer fuel gas collecting cavity and an inner fuel gas collecting cavity is adjusted through a fuel flow distributor, and the oxidant flow entering an outer oxidant channel (or an outer oxidant gas collecting cavity) and an inner oxidant gas collecting cavity is adjusted through an oxidant flow distributor, so that an independent tangential unstable combustion mode, an independent continuous rotary detonation mode and a composite mode can be realized.

The method for realizing the single tangential unstable combustion mode comprises the following steps: all the fuel flow enters the inner fuel gas collecting cavity by controlling the fuel flow distributor and enters the combustion chamber through the coaxial shear type nozzle. Meanwhile, by controlling the flow distributor of the oxidant, all the oxidant flows enter the inner oxidant gas-collecting cavity and enter the combustion chamber through the inner oxidant channel, namely the nozzle mode. The fuel and oxidant entering the combustion chamber are mixed and ignited by matching with an electric spark igniter, so that a tangential unstable combustion mode is realized.

The method for realizing the single continuous rotation knocking mode comprises the following steps: all the flow rate of fuel enters the outer fuel gas-collecting cavity by controlling the fuel flow rate distributor and enters the combustion chamber through a plurality of outer fuel channels, and all the flow rate of oxidant enters the outer oxidant gas-collecting cavity by controlling the oxidant flow rate distributor and enters the combustion chamber through the outer oxidant channels, namely, a circumferential seam injection mode. The fuel and oxidant entering the combustion chamber are mixed and cooperate with the tangential hot jet igniter to ignite, thereby realizing a continuous rotation detonation mode.

The method for realizing the composite mode comprises the following steps: the mass flow ratio of the fuel in the outer fuel gas-collecting cavity and the inner fuel gas-collecting cavity is controlled by the fuel flow distributor, so that part of the fuel enters the inner fuel gas-collecting cavity, and the other part of the fuel enters the outer fuel gas-collecting cavity.

The mass flow ratio of the oxidant in the outer oxidant gas-collecting cavity and the inner oxidant gas-collecting cavity is controlled by the oxidant flow distributor, so that part of the oxidant flows into the inner fuel gas-collecting cavity and the inner oxidant channel, and the other part of the oxidant flows into the outer oxidant gas-collecting cavity and the outer oxidant channel.

The fuel entering the inner fuel gas-collecting cavity passes through the coaxial shear type nozzle, is mixed with the oxidant sprayed from the inner oxidant channel, enters the combustion chamber, and is matched with the electric spark igniter to ignite, so that the tangential unstable combustion mode is realized.

The fuel entering the outer fuel gas-collecting cavity passes through the outer fuel channel, is mixed with the oxidant sprayed from the outer oxidant channel, enters the combustion chamber, and is ignited by matching with the tangential thermal jet igniter, so that the continuous rotation detonation mode is realized.

The mass flow ratio of the corresponding propellant is adjusted by adjusting the fuel flow distributor and the oxidant flow distributor, so that the relation and the transformation rule of tangential unstable combustion and continuous rotation detonation can be continuously observed, and the unstable excitation mechanism of the tangential combustion of the liquid rocket engine is explained by utilizing the rotation detonation theory.

In addition, when all the flow is injected through the circumferential seam injection mode, the detonation ignition is carried out by matching with the tangential hot jet igniter 9, a continuous rotation detonation combustion mode is excited, the flow distribution device is adjusted, the flow of the nozzle injection mode is gradually increased, and the combustion state is gradually transited to the rocket engine working mode.

Further, when all the flow is injected through a nozzle injection mode, the rocket engine isobaric combustion mode is excited by matching with ignition of the electric spark igniter 10, the flow distributor is adjusted to gradually increase the flow of the circumferential seam injection mode, and the combustion state has the characteristic of continuous rotation detonation.

Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.