Turbo-ramjet combined engine and control method thereof

Abstract

The invention belongs to the technical field of design of turbo-ramjet combination engines, and particularly relates to a turbo-ramjet combination engine and a control method thereof. According to the design, a complex outer turbine channel is separated from a smooth ramjet channel, and an afterburner and a ramjet combustion chamber are designed to share the space; the designed center stamping channel has multiple functions of a turbine engine stator force bearing frame, a center deflation channel, a subsonic combustion stamping rectification channel, a scramjet channel and the like. Self-adaptive switching of four working modes including a turbine engine conventional working mode, a turbine engine center deflation working mode, a subsonic combustion stamping working mode and a scramjet working mode is achieved, the space of a center stamping channel is utilized to the maximum extent, the working speed range of the turbine modes is widened, the cross sectional area is greatly reduced, the flight resistance is effectively reduced, and the service life of the turbine engine is prolonged. And wide-speed-range work with the Mach number of 0-7 is realized.

Description

Technical Field

[0001] The present application belongs to the technical field of turboramjet combination engine design, and specifically relates to a turboramjet combination engine and a control method thereof. Background Art

[0002] The turboramjet combined power has the characteristics of high comprehensive specific impulse, good reusability, easy use and maintenance, and low operating cost. It is an ideal power for hypersonic aircraft.

[0003] According to the different combinations of turbine engines and ramjet engines, turboramjet combination power can be divided into tandem turboramjet combination engine and parallel turboramjet combination engine. Among them, the tandem turboramjet combination engine shares the space of the ramjet engine combustion chamber and the turbine engine afterburner combustion chamber, and has a smaller cross-sectional area and lower resistance than the parallel turboramjet combination engine.

[0004] The Mach 5 turboramjet combination engine adopts a subsonic ramjet as the high-speed power. The flow inside the subsonic ramjet engine is subsonic, and the complex outer duct surface of the turbine engine can be used as the intake duct of the subsonic ramjet. Therefore, the Mach 5 turboramjet combination engine can adopt a tandem turboramjet combination engine configuration to have lower resistance.

[0005] The Mach 7 turboramjet combination engine uses scramjet as the high-speed power. The inside of the scramjet engine is supersonic flow, and the complex external surface of the turbine engine cannot form the smooth wall required for the scramjet intake. Therefore, the Mach 7 combined power engine generally adopts a parallel turboramjet combination engine configuration, which has a large resistance.

[0006] For the Mach 7 turboramjet combination engine, due to the temperature resistance of the material and the working characteristics of the compression components, the upper limit of the working speed range of the turbine engine is Mach 3.2-3.5, while the lower limit of the working speed range of the super ramjet engine is Mach 4-5. The two need to adopt certain speed range connection methods. In this regard, at present, most of them set up a pre-cooling system to expand the working envelope of the turbine engine and increase the upper limit of the working speed range of the turbine engine. This technical solution will greatly increase the complexity of the overall structure and will greatly increase the weight of the turboramjet combination engine. Alternatively, a sub-combustion channel is added outside the turbine engine to change it to a Mach 5 stage tandem turboramjet combination engine. This technical solution will further increase the cross-sectional area of ​​the turboramjet combination engine, resulting in increased resistance, and greatly increase the weight of the turboramjet combination engine, reducing the thrust-to-weight ratio of the turboramjet combination engine.

[0007] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0008] The purpose of the present application is to provide a turboramjet combination engine and a control method thereof to overcome or alleviate at least one aspect of the known technical deficiencies.

[0009] The technical solution of this application is:

[0010] On the one hand, a turboramjet combination engine is provided, comprising an air inlet, a turbine engine, and an afterburner / ramjet dual-mode combustion chamber;

[0011] An intake cone is arranged in the intake duct;

[0012] The turbine engine is arranged after the air inlet and includes a rotor component and a stator component;

[0013] The rotor parts of a turbine engine include a drum-type rotor casing, a compressor rotor, and a turbine rotor. The front end of the drum-type rotor casing is connected to the rear end of the air inlet, and the middle part is in a drum shape; the compressor rotor is connected to the front end of the drum-type rotor casing; and the turbine rotor is connected to the rear end of the drum-type rotor casing.

[0014] The stator components of a turbine engine include a stator casing, a compressor stator, a turbine stator, and a main combustion chamber. The stator casing is arranged inside the drum-type rotor casing, and an outer turbine channel is formed between the stator casing and the drum-type rotor casing, and a ram channel is formed inside. The ram channel is a gradually expanding channel; the compressor stator is connected to the front end of the stator casing, and forms a compressor with the compressor rotor; the turbine stator is connected to the rear end of the stator casing, and forms a turbine with the turbine rotor; the main combustion chamber is connected to the middle part of the stator casing, and is located in the drum-shaped part of the drum-type rotor casing;

[0015] The stator casing has a plurality of circumferentially distributed air inlet holes at the intermediate stage of the compressor stator, each of which is equipped with an air inlet valve, and each of which can be opened and closed in the air inlet hole;

[0016] The front end of the stator casing is hinged with multiple adjustable plates. When the adjustable plates are opened outward, the front ends can be pressed against the inner side of the air inlet to block the inlet of the outer turbine channel. When they are retracted inward, the front ends can be placed on the air inlet cone to block the inlet of the ram channel.

[0017] The afterburner / ramjet dual-mode combustion chamber is arranged behind the turbine engine, including an annular outer wall and an inner cone, wherein the front end of the annular outer wall is connected to the rear end of the drum-type rotor casing; the inner cone is arranged inside the annular outer wall, and is composed of a plurality of adjustment plates, each of which is hinged at the rear end of the stator casing. When it is opened outward, the rear end can be pressed against the inner side of the annular outer wall to block the outlet of the outer turbine channel; when it is contracted inward, the rear end can be spliced ​​into a cone to block the outlet of the ramjet channel. In addition, the front end of the inner cone has a plurality of injection holes distributed along the circumferential direction, and each injection hole is equipped with an injection valve, and each injection valve can be opened and closed in the injection hole.

[0018] According to at least one embodiment of the present application, in the above-mentioned turboramjet combination engine, a plurality of peripheral flame stabilizers are arranged along the circumferential direction on the inner side of the annular outer wall;

[0019] A plurality of inner circumferential flame stabilizers are arranged along the circumferential direction on the outer side of the inner cone.

[0020] According to at least one embodiment of the present application, the above-mentioned turboramjet combination engine further includes a tail nozzle;

[0021] The tail nozzle is arranged behind the afterburner / ramjet dual-mode combustion chamber, and comprises a convergent section and an expansion section, wherein the front end of the convergent section is hinged to the rear end of the annular outer wall, and the front end of the expansion section is hinged to the rear end of the convergent section.

[0022] According to at least one embodiment of the present application, the above-mentioned turboramjet combined engine has:

[0023] In the normal working mode of the turbine engine, each adjustable plate is retracted inwards, each air induction valve is closed in the air induction hole, each regulating plate is retracted inwards, and each ejection valve is closed in the ejection hole;

[0024] In the central bleed working mode of the turbine engine, each adjustable plate is retracted inwards, each bleed valve is opened in the bleed hole, each regulating plate is retracted inwards, and each ejection valve is opened in the ejection hole;

[0025] In the sub-combustion ramjet working mode, each adjustable plate expands outward, each air induction valve is closed in the air induction hole, each regulating plate contracts inward, and each ejection valve is opened in the ejection hole;

[0026] In the scramjet operating mode, each adjustable plate expands outward, each air induction valve is closed in the air induction hole, each regulating plate expands outward, and each ejection valve is closed in the ejection hole.

[0027] According to at least one embodiment of the present application, in the above-mentioned turboramjet combination engine, when the turboramjet combination engine is in the conventional working mode of the turbine engine, the center bleed working mode of the turbine engine, and the scramjet working mode, the throat of the tail nozzle contracts; when it is in the scramjet working mode, the throat of the tail nozzle expands.

[0028] On the other hand, a turboramjet combination engine control method is provided, which is used to control the turboramjet combination engine, comprising:

[0029] In the Mach number 0-2 speed range, the turboramjet combination engine is set to be in the conventional working mode of the turbine engine;

[0030] In the speed range of Mach number 2-3.2, the turboramjet combination engine is set to be in the turbine engine center bleed working mode;

[0031] In the Mach number range of 3.2-5, the turboramjet engine is set to be in the sub-ramjet working mode;

[0032] In the Mach number range of 5-7, the turboramjet combination engine is set in the scramjet working mode.

[0033] This application has at least the following beneficial technical effects:

[0034] Provided are a turboramjet combined engine and a control method thereof. The complex outer turbine channel is separated from the smooth ramjet channel in a design, and the afterburner chamber and the ramjet chamber are designed to share space. The central ramjet channel is designed to have multiple functions such as a turbine engine stator load-bearing frame, a central air bleed channel, a subcombustion ramjet rectifying channel, and a scramjet channel, so as to realize adaptive switching of four working modes, namely, a conventional working mode of a turbine engine, a central air bleed working mode of a turbine engine, a subcombustion ramjet working mode, and a scramjet working mode. The space of the central ramjet channel is utilized to the maximum extent, the cross-sectional area is greatly reduced, the flight resistance is effectively reduced, and the operation in a wide speed range of Mach number 0-7 is realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 is a schematic diagram of a turboramjet combination engine provided in an embodiment of the present application;

[0036] Figure 2 is a schematic diagram of a turbine engine rotor component provided in an embodiment of the present application;

[0037] Figure 3 is a schematic diagram of a turbine engine stator component provided in an embodiment of the present application;

[0038] Figure 4 is a schematic diagram of an afterburner / ramjet dual-mode combustion chamber (3) provided in an embodiment of the present application;

[0039] Figure 5 is a schematic diagram of a turboramjet combination engine provided by an embodiment of the present application in a conventional working mode of a turbine engine;

[0040] Figure 6 is a schematic diagram of a turboramjet combination engine provided by an embodiment of the present application in a turbine engine center bleed working mode;

[0041] Figure 7 is a schematic diagram of a turboramjet combination engine provided by an embodiment of the present application in a sub-combustion ramjet working mode;

[0042] Figure 8 is a schematic diagram of a turboramjet combination engine provided in an embodiment of the present application in a scramjet working mode;

[0043] in:

[0044] 1-intake duct; 2-turbine engine; 3-afterburner / ramjet dual-mode combustion chamber; 4-tail nozzle; 5-intake cone; 6-rotor component; 7-stator component; 8-drum rotor casing; 9-compressor rotor; 10-turbine rotor; 11-stator casing; 12-compressor stator; 13-turbine rotor; 14-main combustion chamber; 15-adjustable plate; 16-annular outer wall; 17-inner cone; 18-peripheral flame stabilizer; 19-inner flame stabilizer; 20-injection valve; 21-injection valve.

[0045] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0046] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0047] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0048] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0049] Scramjet requires an expansion channel. The exit cross-sectional area of ​​the Mach 7-stage parallel turboramjet combination engine is the largest, while the inlet has a large surplus space, low space utilization, and excessive flight resistance. If the afterburner behind the turbine engine and the scramjet combustion chamber can share space, the maximum cross-sectional area of ​​the turboramjet combination engine will be determined by the inlet cross-sectional area of ​​the turbine engine and the ramjet engine, avoiding space waste at the inlet. Based on this, the embodiment of the present application provides a turboramjet combination engine, such as Figure 1 As shown, it includes an air inlet 1, a turbine engine 2, an afterburner / ramjet dual-mode combustion chamber 3, and a tail nozzle 4.

[0050] An intake cone 5 is arranged in the intake passage 1 .

[0051] The turbine engine 2 is arranged after the air inlet 1 and adopts a single-rotor turbojet engine with central air discharge, including a rotor component 6 and a stator component 7.

[0052] The rotor component 6 of the turbine engine 2 is as follows Figure 2 As shown, it includes a drum-type rotor casing 8, a compressor rotor 9, and a turbine rotor 10, wherein the front end of the drum-type rotor casing 8 is connected to the rear end of the air inlet 1, and the middle part is drum-shaped; the compressor rotor 9 is connected to the front end of the drum-type rotor casing 8; and the turbine rotor 10 is connected to the rear end of the drum-type rotor casing 8.

[0053] The stator component 7 of the turbine engine 2 is as follows Figure 3 As shown, it includes a stator casing 11, a compressor stator 12, a turbine stator 13, and a main combustion chamber 14, wherein the stator casing 11 is arranged on the inner side of the drum rotor casing 8, and forms an outer turbine channel between the stator casing 11 and the drum rotor casing 8, and a ram channel is formed inside, and the ram channel is a gradually expanding channel; the compressor stator 12 is connected to the front end of the stator casing 11, and forms a compressor with the compressor rotor 9; the turbine stator 13 is connected to the rear end of the stator casing 11, and forms a turbine with the turbine rotor 10; the main combustion chamber 14 is connected to the middle part of the stator casing 11, and is located in the drum-shaped part of the drum rotor casing 8. In addition, the stator casing 11 has a plurality of circumferentially distributed air inlet holes at the compressor rotor 9, and each air inlet hole is installed with an air inlet valve 21, and each air inlet valve 21 can be opened and closed in the air inlet, and can be driven by an actuator.

[0054] A plurality of adjustable plates 15 are hinged at the front end of the stator casing 11. When each adjustable plate 15 is opened outward, the front end can be pressed against the inner side of the air inlet 1 to block the inlet of the outer turbine channel. When it is retracted inward, the front end can be placed on the air inlet cone 5 to block the inlet of the ram channel. Specifically, an actuator can be set to drive it.

[0055] The afterburner / ramjet dual-mode combustion chamber 3 is arranged behind the turbine engine 2. Figure 4 As shown, it includes an annular outer wall 16 and an inner cone 17, wherein the front end of the annular outer wall 16 overlaps with the rear end of the drum-type rotor casing 8, and a plurality of outer peripheral flame stabilizers 18 are arranged circumferentially on the inner side; the inner cone 17 is arranged inside the annular outer wall 16, and a plurality of inner peripheral flame stabilizers 19 are arranged circumferentially on the outer side, and the inner cone 17 is composed of a plurality of adjustment plates, each of which is hinged at the rear end of the stator casing 11. When it is opened outward, the rear end can be pressed against the inner side of the annular outer wall 16 to block the outlet of the outer turbine channel. When it is contracted inward, the rear end can be spliced ​​into a cone to block the outlet of the stamping channel. Specifically, an actuator can be arranged to drive it. In addition, the front end of the inner cone 17 has a plurality of ejection holes distributed along the circumferential direction, and an ejection valve 20 is installed in each ejection hole. Each ejection valve 20 can be opened and closed in the ejection hole, and specifically, an actuator can be arranged to drive it.

[0056] The tail nozzle 4 is arranged behind the afterburner / ramjet dual-mode combustion chamber 3, and includes a convergent section and an expansion section, wherein the front end of the convergent section is hinged to the rear end of the annular outer wall 16, and the front end of the expansion section is hinged to the rear end of the convergent section. An actuator can be set to drive the throat to contract or expand.

[0057] The above-mentioned turboramjet combination engine can be designed to have a conventional turbine engine operating mode, a center bleed turbine engine operating mode, a subsonic ramjet operating mode, and a scramjet operating mode.

[0058] When the turboramjet engine is in the normal working mode of the turbo engine, each adjustable plate 15 shrinks inwards, each air inlet valve 21 is closed in the air inlet hole, each regulating plate shrinks inwards, each ejection valve 20 is closed in the ejection hole, and the throat of the tail nozzle 4 shrinks. Figure 5 shown.

[0059] When the turboramjet engine is in the turbine engine center exhaust mode, each adjustable plate 15 contracts inwards, each air inlet valve 21 opens in the air inlet hole, each regulating plate contracts inwards, each ejection valve 20 opens in the ejection hole, and the throat of the tail nozzle 4 contracts. Figure 6 shown.

[0060] When the turboramjet engine is in the sub-combustion ramjet working mode, each adjustable plate 15 expands outward, each air inlet valve 21 is closed in the air inlet hole, each regulating plate shrinks inward, each ejection valve 20 is opened in the ejection hole, and the throat of the tail nozzle 4 shrinks. Figure 7 Shown

[0061] When the turboramjet engine is in the scramjet working mode, each adjustable plate 15 expands outwards, each air inlet valve 21 is closed in the air inlet hole, each regulating plate expands outwards, each ejection valve 20 is closed in the ejection hole, and the throat of the tail nozzle 4 expands. Figure 8 shown.

[0062] Based on the turboramjet combination engine disclosed in the above implementation, the present application provides a turboramjet combination engine control method to achieve flight in a wide speed range of Mach numbers 0-7.

[0063] In the Mach number speed range of 0-2, the turbine engine has a good specific impulse, and the turboramjet combination engine can be set in the normal working mode of the turbine engine. At this time, the air is taken in by the air inlet 1, completely passes through the external turbine channel, and is supplied to the turbine engine 2, and burns in the main combustion chamber 14 and the afterburner / ramjet dual-mode combustion chamber 3, which is the turbine engine working mode.

[0064] After the Mach number exceeds 2, the intake temperature gradually increases, and the compressor in the turbine engine 2 will be blocked, unable to allow too much airflow to flow through, resulting in a reduction in the thrust of the turboramjet combination engine. At this time, the turboramjet combination engine can be set to a central bleed working mode of the turbine engine, and part of the gas in the outer turbine channel is introduced into the ramjet channel through the air bleed holes, and then injected into the afterburner / ramjet dual-mode combustion chamber 3 through the injection holes for combustion. This can extend the upper limit of the operating speed of the turbine engine 2 and improve the thrust of the turbine engine in the high Mach state, which is the turbine engine working mode.

[0065] When the Mach number exceeds 3.2, it will exceed the upper limit of the turbine engine's working capacity. At this time, the turboramjet combination engine can be set to a sub-combustion ramjet working mode. Air enters the inlet 1 and completely enters the ramjet channel. It is ejected through the ejection hole into the afterburner / ramjet dual-mode combustion chamber 3 for combustion. This is the sub-combustion ramjet engine working mode, which can increase the working speed range to Mach number 5.

[0066] When the Mach number exceeds 5, the efficiency of the scramjet engine will be greatly reduced. At this time, the turboramjet combination engine can be set in the scramjet working mode. The intake air of the inlet 1 completely enters the ramjet channel, passes through the expansion smooth flow channel, and enters the afterburner / ramjet dual-mode combustion chamber 3 for combustion. This is the scramjet engine working mode, and the working speed range can be increased to Mach number 7.

[0067] The turboramjet combination engine and control method disclosed in the above-mentioned embodiment are designed to separate the complex outer turbine channel from the smooth ramjet channel, and the afterburner combustion chamber and the ramjet combustion chamber are designed to share the space. The central ramjet channel is designed to have multiple functions such as the turbine engine stator load-bearing frame, the central air bleed channel, the subcombustion ramjet rectifying channel, and the scramjet channel, so as to realize adaptive switching of four working modes, namely the conventional working mode of the turbine engine, the central air bleed working mode of the turbine engine, the subcombustion ramjet working mode, and the scramjet working mode, and maximize the use of the space of the central ramjet channel, greatly reduce the cross-sectional area, effectively reduce the flight resistance, and realize the wide speed range operation of Mach number 0-7.

[0068] The turboramjet combination engine and control method disclosed in the above-mentioned embodiment are designed based on an exoskeleton structure to design a turboramjet combination power with central air release and speed expansion domain and afterburner / ramjet multi-mode combustion chamber characteristics. The design adopts a drum-type rotor configuration to eliminate the heavy disk and shaft in the center of the traditional turbine engine. The rotor component 6 is suspended from the outside to the inside to form a smooth central channel in the center of the turbine engine, creating conditions for the turbine engine bleed air, sub-combustion ramjet intake and super-combustion ramjet intake, and the afterburner / ramjet dual-mode combustion chamber 3 is designed to have multiple modes of afterburner and ramjet. At the same time, the flame stabilizer is designed to be divided into a shorter peripheral flame stabilizer 18 and an inner peripheral flame stabilizer 19, so as to ensure the flame stabilization effect while avoiding interference with switching between working modes.

[0069] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A turboramjet engine, characterized in that: It comprises an air inlet (1), a turbine engine (2), and an afterburner / ramjet dual-mode combustion chamber (3); An air intake cone (5) is arranged in the air intake passage (1); The turbine engine (2) is arranged behind the air inlet (1), and comprises a rotor component (6) and a stator component (7); The rotor component (6) of the turbine engine (2) comprises a drum-type rotor casing (8), a compressor rotor (9), and a turbine rotor (10), wherein the front end of the drum-type rotor casing (8) is connected to the rear end of the air inlet (1), and the middle part is in a drum shape; the compressor rotor (9) is connected to the front end of the drum-type rotor casing (8); and the turbine rotor (10) is connected to the rear end of the drum-type rotor casing (8); The stator component (7) of the turbine engine (2) comprises a stator casing (11), a compressor stator (12), a turbine stator (13), and a main combustion chamber (14), wherein the stator casing (11) is arranged on the inner side of a drum-type rotor casing (8), and an outer turbine channel is formed between the stator casing (11) and the drum-type rotor casing (8), and a ram channel is formed inside the stator casing (11), and the ram channel is a gradually expanding channel; the compressor stator (12) is connected to the front end of the stator casing (11), and forms a compressor with the compressor rotor (9); the turbine stator (13) is connected to the rear end of the stator casing (11), and forms a turbine with the turbine rotor (10); the main combustion chamber (14) is connected to the middle part of the stator casing (11), and is located in the drum-shaped part of the drum-type rotor casing (8); The stator casing (11) has a plurality of bleed holes distributed along the circumferential direction at the middle stage of the compressor stator (12), each bleed hole being equipped with an bleed valve (21), and each bleed valve (21) can be opened and closed in the bleed hole; A plurality of adjustable plates (15) are hingedly connected to the front end of the stator casing (11). When the adjustable plates (15) are opened outward, the front ends can be pressed against the inner side of the air inlet (1) to block the inlet of the outer turbine channel. When the adjustable plates (15) are retracted inward, the front ends can be placed on the air inlet cone (5) to block the inlet of the ram channel. The afterburner / ramjet dual-mode combustion chamber (3) is arranged behind the turbine engine (2), and comprises an annular outer wall (16) and an inner cone (17), wherein the front end of the annular outer wall (16) overlaps the rear end of the drum-type rotor casing (8); the inner cone (17) is arranged inside the annular outer wall (16), and is composed of a plurality of adjustment plates, each of which is hinged to the rear end of the stator casing (11). When the adjustment plates are opened outward, the rear end can press against the inner side of the annular outer wall (16) to block the outlet of the outer turbine channel; when the adjustment plates are contracted inward, the rear end can be spliced ​​into a cone to block the outlet of the ramjet channel. In addition, the front end of the inner cone (17) has a plurality of ejection holes distributed along the circumferential direction, and each ejection hole is installed with an ejection valve (20), and each ejection valve (20) can be opened and closed in the ejection hole.

2. The turboramjet engine according to claim 1, characterized in that: A plurality of peripheral flame stabilizers (18) are arranged along the circumferential direction on the inner side of the annular outer wall (16); A plurality of inner circumferential flame stabilizers (19) are arranged along the circumferential direction on the outer side of the inner cone (17).

3. The turboramjet engine according to claim 1, characterized in that: Also includes a tail nozzle (4); The tail nozzle (4) is arranged behind the afterburner / ramjet dual-mode combustion chamber (3), and comprises a convergent section and an expansion section, wherein the front end of the convergent section is hinged to the rear end of the annular outer wall (16), and the front end of the expansion section is hinged to the rear end of the convergent section.

4. The turboramjet combination engine according to claim 1, characterized in that: The turboramjet engine has: In the conventional working mode of the turbine engine, each adjustable plate (15) is retracted inwardly, each air induction valve (21) is closed in the air induction hole, each regulating plate is retracted inwardly, and each ejection valve (20) is closed in the ejection hole; In the central exhaust working mode of the turbine engine, each adjustable plate (15) is retracted inwardly, each air induction valve (21) is opened in the air induction hole, each regulating plate is retracted inwardly, and each ejection valve (20) is opened in the ejection hole; In the sub-combustion ramjet working mode, each adjustable plate (15) expands outward, each air induction valve (21) is closed in the air induction hole, each regulating plate contracts inward, and each ejection valve (20) is opened in the ejection hole; In the scramjet working mode, each adjustable plate (15) expands outwards, each air induction valve (21) is closed in the air induction hole, each regulating plate expands outwards, and each ejection valve (20) is closed in the ejection hole.

5. The turboramjet combination engine according to claim 4, characterized in that: When the turboramjet combined engine is in a conventional turboengine working mode, a central exhaust working mode, or a scramjet working mode, the throat of the tail nozzle (4) contracts; when it is in a scramjet working mode, the throat of the tail nozzle (4) expands.

6. A turboramjet control method for controlling the turboramjet according to claim 1, characterized in that: include: In the Mach number 0-2 speed range, the turboramjet combination engine is set to be in the conventional working mode of the turbine engine; In the speed range of Mach number 2-3.2, the turboramjet combination engine is set to be in the turbine engine center bleed working mode; In the Mach number range of 3.2-5, the turboramjet engine is set to be in the sub-ramjet working mode; In the Mach number range of 5-7, the turboramjet combination engine is set in the scramjet working mode.

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