A turboramjet combination engine and control method thereof

Abstract

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. The design separates the complex outer turbine channel from the smooth ramjet channel, and the design shares the space between the afterburner and the ramjet combustion chamber. The design of the central ramjet channel has multiple functions such as the turbine engine stator load-bearing frame, the central bleed channel, the subsonic ramjet rectifier channel, and the scramjet channel, thereby realizing adaptive switching of the four working modes of the turbine engine conventional working mode, the turbine engine central bleed working mode, the subsonic ramjet working mode, and the scramjet working mode. The space of the central ramjet channel is utilized to the greatest extent, so that the turbine mode working speed range is widened and the cross-sectional area is greatly reduced, thereby effectively reducing the flight resistance and realizing a wide speed range operation of Mach number 0-7.

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 series turboramjet combination engine and parallel turboramjet combination engine. Among them, the series turboramjet combination engine shares the space of the ramjet engine combustion chamber and the turbine engine afterburner combustion chamber. Compared with the parallel turboramjet combination engine, it has a smaller cross-sectional area and lower resistance.

[0004] The Mach 5 turboramjet combination engine uses 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 series turboramjet combination engine configuration to have lower resistance.

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

[0006] For a Mach 7 turboramjet combination engine, due to the limitations of the material's temperature resistance and the working characteristics of the compression components, the upper limit of the turboengine's operating speed range is Mach 3.2-3.5, while the lower limit of the super-ramjet's operating speed range is Mach 4-5. The two need to adopt certain speed range connection methods. To this end, currently, most of the methods are to set up a pre-cooling system to expand the turboengine's operating envelope and increase the upper limit of the turboengine's operating speed range. This technical solution will greatly increase the complexity of the overall structure and significantly increase the weight of the turboramjet combination engine. Alternatively, a sub-combustion channel is added outside the turboengine 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 of the technical deficiencies of the known ones.

[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 components of a turbine engine include a drum rotor case, a compressor rotor, and a turbine rotor. The front end of the drum rotor case is connected to the rear end of the air inlet, and the middle part is drum-shaped; the compressor rotor is connected to the front end of the drum rotor case; and the turbine rotor is connected to the rear end of the drum rotor case.

[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 rotor casing, forming an outer turbine channel with the drum rotor casing, and a ram channel inside, which 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 inside the drum-shaped part of the drum 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 capable of opening and closing 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 press against the inner side of the air inlet, blocking the inlet of the outer turbine channel. When they are retracted inward, the front ends can rest on the air inlet cone, blocking 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 multiple adjustment plates, each of which is hinged to 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 multiple injection holes distributed along the circumference, and each injection hole is installed 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 provided 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 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, 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 combination 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 turbine engine center bleed mode, 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 inlet valve is closed in the air inlet 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, the tail nozzle throat contracts when the turboramjet combination engine is in the conventional operating mode of the turbine engine, the center bleed operating mode of the turbine engine, and the scramjet operating mode; and the tail nozzle throat expands when the turboramjet combination engine is in the scramjet operating mode.

[0028] Another aspect provides a turboramjet control method for controlling the turboramjet, comprising:

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

[0030] In the Mach 2-3.2 speed range, the turboramjet is set to the turbine engine center bleed mode;

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

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

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

[0034] Provided are a turboramjet combination engine and a control method thereof. The design separates a complex outer turbine channel from a smooth ramjet channel, and the design shares the space between the afterburner and the ramjet chamber. The design includes a central ramjet channel having multiple functions such as a turbine engine stator load-bearing frame, a central bleed channel, a subsonic ramjet rectifying channel, and a scramjet channel. Adaptive switching of four operating modes, namely, a conventional turbine engine operating mode, a turbine engine central bleed operating mode, a subsonic ramjet operating mode, and a scramjet operating mode, is achieved. The space of the central ramjet channel is utilized to the greatest extent, the cross-sectional area is greatly reduced, the flight resistance is effectively reduced, and operation in a wide speed range of Mach numbers of 0-7 is achieved. 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 by an embodiment of the present application;

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

[0038] Figure 4 Schematic diagram of the 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 turbine engine operating mode;

[0040] Figure 6 Schematic diagram of a turboramjet engine provided by an embodiment of the present application in a turbine engine center bleed operating mode;

[0041] Figure 7 Schematic diagram of a turboramjet engine provided by an embodiment of the present application in a sub-ramjet operating mode;

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

[0043] in:

[0044] 1-inlet duct; 2-turbine engine; 3-afterburner / ramjet dual-mode combustion chamber; 4-tail nozzle; 5-inlet 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-outer peripheral flame stabilizer; 19-inner peripheral flame stabilizer; 20-injection valve; 21-induction 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 should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0046] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant 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 should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application 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 means 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 stipulated 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 cross-sectional area at the outlet of a Mach 7-stage parallel turboramjet combination engine is the largest, while there is a large surplus of space at the inlet, resulting in 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, thus avoiding space waste at the inlet. Based on this, an 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 provided in the intake duct 1 .

[0051] The turbine engine 2 is arranged behind the air inlet 1 and adopts a single-rotor turbojet engine with central bleed, 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. The stator casing 11 is arranged inside the drum rotor casing 8, forming an outer turbine channel between the stator casing 11 and the drum rotor casing 8, and a ram channel inside the stator casing 11, which 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 bleed holes at the compressor rotor 9. Each air bleed hole is installed with an air bleed valve 21. Each air bleed valve 21 can be opened and closed in the air bleed hole, and can be driven by an actuator.

[0054] The front end of the stator casing 11 is hinged with multiple adjustable plates 15. 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. An actuator can be set to drive it.

[0055] The afterburner / ramjet dual-mode combustion chamber 3 is set behind the turbine engine 2, as shown in FIG. 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 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 to 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 set to drive it. In addition, the front end of the inner cone 17 has a plurality of ejection holes distributed along the circumference, 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 set 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 is in the normal working mode of the turbo engine, each adjustable plate 15 is retracted inwards, each air inlet valve 21 is closed in the air inlet hole, each regulating plate is retracted inwards, each ejection valve 20 is closed in the ejection hole, and the throat of the tail nozzle 4 is retracted. Figure 5 shown.

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

[0060] When the turboramjet engine is in the sub-ramjet working mode, each adjustable plate 15 expands outward, each air inlet valve 21 is closed in the air inlet hole, each regulating plate contracts inward, each ejection valve 20 is opened in the ejection hole, and the throat of the tail nozzle 4 contracts. 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 piece expands outwards, each ejection valve 20 is closed in the ejection hole, and the tail nozzle 4 throat expands. Figure 8 shown.

[0062] Based on the turboramjet combination engine disclosed in the above embodiment, 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 to the conventional 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 the turbine engine center bleed working mode, and part of the gas in the outer turbine channel is introduced into the ramjet channel through the bleed holes, and then injected into the afterburner / ramjet dual-mode combustion chamber 3 through the injection holes for combustion. In this way, the upper limit of the operating speed of the turbine engine 2 can be extended, and the thrust of the turbine engine in the high Mach state can be improved, 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 the sub-ramjet working mode. The air enters the air 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-ramjet engine working mode, which can increase the working speed range to Mach 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 to the scramjet working mode. The intake air of the inlet 1 completely enters the ramjet channel, passes through the expansion-type smooth flow channel, and enters the afterburner / ramjet dual-mode combustion chamber 3 for combustion. This is the scramjet engine working mode, which can increase the working speed range to Mach number 7.

[0067] The turboramjet combination engine and control method disclosed in the above embodiments 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 space. The central ramjet channel is designed to have multiple functions such as the turbine engine stator load-bearing frame, the central bleed channel, the subsonic ramjet straightening channel, and the scramjet channel, so as to realize adaptive switching among the four operating modes of the turbine engine conventional operating mode, the turbine engine central bleed operating mode, the subsonic ramjet operating mode, and the scramjet operating mode, maximize the use of the space of the central ramjet channel, greatly reduce the cross-sectional area, effectively reduce the flight resistance, and realize operation in a wide speed range of Mach numbers of 0-7.

[0068] The turboramjet combination engine and control method disclosed in the above embodiment are designed based on an exoskeleton structure to design a turboramjet combination power with central air discharge expansion domain and afterburner / ramjet multi-mode combustion chamber characteristics. The design adopts a drum 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, while ensuring 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 replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A turboramjet engine, characterized in that: It includes 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 duct (1); The turbine engine (2) is arranged behind the air inlet (1) and includes a rotor component (6) and a stator component (7); The rotor component (6) of the turbine engine (2) 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 portion 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) 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 a drum-type rotor casing (8), and forms an outer turbine channel between the stator casing (11) and the drum-type rotor casing (8), and forms a ram channel inside the stator casing, which 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), and each bleed hole is equipped with an bleed valve (21), and each bleed valve (21) can be opened and closed in the bleed hole; The front end of the stator casing (11) is hinged with a plurality of adjustable plates (15). When the adjustable plates (15) are opened outward, the front end can press 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 end can rest 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 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); 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 an ejection valve (20) is installed in each ejection hole. Each ejection valve (20) can be opened and closed in the ejection hole.

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

3. The turboramjet combination 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 comprises: In the conventional working mode of the turbine engine, each adjustable plate (15) is retracted inwards, each air induction valve (21) is closed in the air induction hole, each regulating plate is retracted inwards, and each ejection valve (20) is closed in the ejection hole; In the turbine engine central bleed working mode, each adjustable plate (15) is retracted inwards, each bleed valve (21) is opened in the bleed hole, each regulating plate is retracted inwards, and each ejection valve (20) is opened in the ejection hole; In the sub-combustion ramjet working mode, each adjustable plate (15) expands outwards, each air induction valve (21) is closed in the air induction hole, each regulating plate contracts inwards, and each ejection valve (20) is opened in the ejection hole; In the scramjet operating mode, each adjustable plate (15) expands outwards, each air induction valve (21) is closed in the air induction hole, each regulating piece 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 turbine engine operating mode, a center bleed turbine engine operating mode, or a scramjet operating mode, the throat of the tail nozzle (4) contracts; when in a scramjet operating mode, the throat of the tail nozzle (4) expands.

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

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