Electromagnetically-driven aero-engine rapid mode switching device and method

Abstract

The invention provides an electromagnetically-driven aero-engine rapid mode switching device and method, and relates to the technical field of aero-engines. According to the device, an air inlet channel annular valve is arranged between an air inlet channel and a turbine-based combustion chamber, the air inlet channel annular valve is matched with the outer wall of a combustion cavity to achieve opening and closing of an overall channel, and meanwhile a pair of annular electromagnets fixed to the air inlet channel and the air inlet channel annular valve are used for driving the air inlet channel annular valve to be opened and closed. According to the method, simple and highly reliable mode switching can be achieved, the millisecond response effect can be achieved, it is ensured that an air inlet outlet is reliably closed at the moment of switching from the air suction mode to the rocket mode, the downstream high-temperature gas backflow risk is thoroughly eliminated, and it is ensured that the pressure of a rocket combustion chamber is instantaneously established. The rapid mode switching device for the aero-engine is low in complexity, high in structural stability and suitable for various aerospace combined propulsion systems.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to an electromagnetic driving aero-engine rapid mode switching device and method. BACKGROUND

[0002] The combination propulsion system of air-breathing engines (such as turbofan, turbojet engines) and rocket engines (such as rocket-based combined cycle engine RBCC) combines the advantages of the two engines at different speeds and altitudes, and is an important development direction of the power system of future high-speed / hypersonic vehicles. When the combination propulsion system is in the air-breathing engine mode, the inlet is the core front component in this mode, which undertakes the key task of capturing, compressing and adjusting the free flow, and ensures that the downstream combustion chamber is supplied with high-pressure gas flow with sufficient flow, stable pressure and uniform flow. The performance directly affects the working efficiency and stability margin of the engine; when the combination propulsion system needs to switch from the air-breathing mode relying on atmospheric oxygen to the pure rocket mode with self-carried oxidizer (such as during the process of crossing the atmosphere boundary, high-speed acceleration or performing specific maneuvers), a necessary and crucial key link is to timely, reliably and quickly close the inlet outlet to prevent the high-pressure hot flow generated by the downstream turbine combustion chamber from flowing backward through the inlet, causing unnecessary structural damage and flight resistance; effective channel closing action can isolate the high-temperature gas environment to protect the precise internal components of the inlet.

[0003] In the prior art, the device for closing the inlet outlet during the mode switching of the combination propulsion system faces challenges such as insufficient response speed, complex structure, and limited reliability. Conventional mechanical valves (such as rotary doors, flap valves, slide valves) and their driving mechanisms (such as hydraulic, pneumatic or motor drives) often have large inertia and driving delays, making it difficult to meet the strict requirements of millisecond-level rapid switching of high-speed vehicles. The slow closing action is easy to cause gas backflow or delay in establishing combustion chamber pressure, threatening system stability and performance. In addition, such valve structures are usually complex and bulky, increasing the weight, volume and complexity of the system, occupying valuable space while reducing overall reliability. In the harsh high-temperature, high-pressure and high-speed gas flow environment of the inlet outlet, the moving parts (such as bearings, seals) are prone to wear and jam, and the dynamic sealing performance is difficult to guarantee in the long term, especially in isolating high-temperature gas. At the same time, the energy consumption of hydraulic or pneumatic drive itself also needs attention. SUMMARY

[0004] The present application relates to the technical field of aero-engines, in particular to an electromagnetic driving aero-engine rapid mode switching device and method.

[0005] Technical solution: An electromagnetic drive aero-engine fast mode switching device, comprising: an air inlet channel, a turbine-based combustion chamber fixedly connected with the air inlet channel; a combustion chamber is arranged in the turbine-based combustion chamber, the combustion chamber is circular in cross section, and a combustion chamber inner passage is formed between the outer wall of the combustion chamber and the inner wall of the turbine-based combustion chamber; an airflow passage is formed between the outer wall of the combustion chamber and the front end inlet of the turbine-based combustion chamber; the airflow passage is in communication with the inside of the air inlet channel; A first annular electromagnet, a second annular electromagnet and an air inlet channel annular valve fixedly connected with the second annular electromagnet are arranged on the periphery of the air inlet channel; the air inlet channel annular valve is cylindrical around the air inlet channel, and the air inlet channel annular valve is inserted from the front end of the turbine-based combustion chamber; the air inlet channel annular valve moves between the first position and the second position through the attraction or repulsion of the first annular electromagnet and the second annular electromagnet; when the air inlet channel annular valve is located at the first position, the first annular electromagnet is close to the second annular electromagnet, so that the air inlet channel, the airflow passage and the combustion chamber inner passage are in communication; when the air inlet channel annular valve is located at the second position, the first annular electromagnet is away from the second annular electromagnet, the rear end of the air inlet channel annular valve is in contact with the outer wall of the combustion chamber, so that the airflow passage and the combustion chamber inner passage are closed.

[0006] Specifically, the air inlet channel comprises an air inlet section and an air outlet section, the radial cross section of the air inlet section is an irregular shape, and the radial cross section of the air outlet section is a circle.

[0007] Specifically, a plurality of groups of sliding rails are arranged on the outer surface of the air inlet channel between the first annular electromagnet and the front end of the turbine-based combustion chamber, and the air inlet channel annular valve is internally provided with sliding blocks sliding on the sliding rails.

[0008] Specifically, the first annular electromagnet is electrically connected with a first electromagnet direct current circuit, and the second annular electromagnet is electrically connected with a second electromagnet direct current circuit.

[0009] Specifically, the outer surface of the air inlet channel is sleeved with an annular flange, and the first annular electromagnet is fixedly connected with the annular flange.

[0010] Specifically, the outer wall of the combustion chamber is in the structure of a barrel, and the bottom of the barrel structure is matched with the rear end of the air inlet channel annular valve.

[0011] Specifically, the bottom of the barrel structure is an outwardly convex conical body, and the half-cone angle of the conical body is 60°.

[0012] The application also provides an aero-engine fast mode switching method using the above-mentioned electromagnetic drive aero-engine fast mode switching device, comprising the following steps: The first annular electromagnet and the second annular electromagnet are electrified, so that the first annular electromagnet and the second annular electromagnet have opposite polarities at the opposite ends, the second annular electromagnet drives the air inlet channel annular valve to move towards the first annular electromagnet, the air inlet channel annular valve is opened, and the aero-engine is switched to the air-breathing engine mode. The first annular electromagnet and the second annular electromagnet are powered on, so that the first annular electromagnet and the second annular electromagnet have the same polarity at opposite ends, the second annular electromagnet drives the air inlet annular valve to move away from the first annular electromagnet until the rear end of the air inlet annular valve is attached to the outer wall of the combustion chamber, the air inlet annular valve is closed, and the aero-engine is switched to a rocket engine mode.

[0013] Specifically, the combustion chamber is filled with rocket fuel, and when the aero-engine is switched to a rocket engine mode, the rocket fuel provides power for the rocket engine mode.

[0014] Specifically, when the aero-engine is switched to a gas suction engine mode, the high-pressure airflow enters the turbine-based combustion chamber through the air inlet and the airflow channel, and the high-pressure airflow is mixed with the fuel in the turbine-based combustion chamber to provide power for the gas suction engine mode.

[0015] Beneficial effects: Compared with the prior art, the significant effect of the present application is that the present application designs a device for rapid mode switching using electromagnetic drive for a combined propulsion system, by arranging an air inlet annular valve between the air inlet and the turbine-based combustion chamber, the air inlet annular valve cooperates with the outer wall of the combustion chamber to realize the opening and closing of the overall air inlet, and by using a pair of annular electromagnets to drive the opening and closing of the air inlet annular valve, simple and highly reliable mode switching can be realized, which can achieve a millisecond-level response effect, ensuring that the air inlet outlet is reliably closed at the moment of switching from the gas suction mode to the rocket mode, completely eliminating the risk of high-temperature gas backflow and ensuring the instantaneous establishment of the rocket combustion chamber pressure. The aero-engine rapid mode switching device provided by the present application has low complexity and high structural stability, and is suitable for various aerospace combined propulsion systems. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a partial cross-sectional view of the aero-engine rapid mode switching device of embodiment 1 of the present application.

[0017] Figure 2 is a perspective view of the aero-engine rapid mode switching device of embodiment 1 of the present application.

[0018] Figure 3 is a schematic diagram of the annular electromagnet actuation principle of the present application.

[0019] Figure 4 is a mode switching schematic diagram of the aero-engine rapid mode switching device of embodiment 2 of the present application. DETAILED DESCRIPTION

[0020] A preferred embodiment of the present application will be further described below with reference to the accompanying drawings.

[0021] Embodiment 1

[0022] Please refer toFigure 1 As shown, the embodiment provides an electromagnetic drive aero-engine fast mode switching device. The mode of the aero-engine includes a rocket engine mode and a air-breathing engine mode. The aero-engine fast mode switching device includes an inlet duct 1 and a turbine-based combustion chamber 6 fixedly connected with the inlet duct 1. The turbine-based combustion chamber 6 is provided with a combustion cavity 51 with a circular cross section. A combustion chamber inner passage 7 is formed between the combustion cavity outer wall 5 and the inner wall of the turbine-based combustion chamber 6. An airflow passage 8 is formed between the combustion cavity outer wall 5 and the front end inlet of the turbine-based combustion chamber 6. The airflow passage 8 is in communication with the inside of the inlet duct 1. The inlet duct 1 is provided with a first annular electromagnet 2, a second annular electromagnet 3, and an inlet duct annular valve 4 fixedly connected with the second annular electromagnet 3. The inlet duct annular valve 4 is a cylinder surrounding the inlet duct 1, and the inlet duct annular valve 4 is inserted from the front end of the turbine-based combustion chamber 6. The inlet duct annular valve 4 moves between a first position and a second position through the attraction or repulsion of the first annular electromagnet 2 and the second annular electromagnet 3. When the inlet duct annular valve 4 is located at the first position, the first annular electromagnet 2 is close to the second annular electromagnet 3, so that the inlet duct 1 inner passage, the airflow passage 8, and the combustion chamber inner passage 7 are in communication. When the inlet duct annular valve 4 is located at the second position, the first annular electromagnet 2 is away from the second annular electromagnet 3, and the rear end of the inlet duct annular valve 4 is in contact with the combustion cavity outer wall 5, so that the airflow passage 8 and the combustion chamber inner passage 7 are closed. Figure 1 The device is shown in the second position.

[0023] In the embodiment, the outer surface of the inlet duct 1 is provided with an annular flange 15. The inlet duct 1 can also be integrally formed by additive manufacturing technology. The first annular electromagnet 2 is fixedly connected with the annular flange 15. The first annular electromagnet 2 and the second annular electromagnet 3 are completely consistent in size and symmetrically arranged. The rear end of the inlet duct 1 is coaxially arranged with the front end of the turbine-based combustion chamber 6 and is fixedly arranged in position.

[0024] Please refer to Figure 1 and Figure 2As shown, in the embodiment, the air inlet passage 1 is composed of two sections with different shapes, i.e. the air inlet section 11 and the air outlet section 12. The radial section of the air inlet section 11 gradually transitions from an irregular shape at the open end to a circular shape at the annular flange 15. The air outlet section 12 is a regular cylindrical structure. The outer diameter of the air outlet section 12 is consistent with the inner diameter of the annular valve 4 of the air inlet passage, and the outer diameter of the annular valve 4 of the air inlet passage is consistent with the inner diameter of the air inlet of the turbine-based combustion chamber 6, so that the annular valve 4 of the air inlet passage can slide between the air inlet passage 1 and the turbine-based combustion chamber 6, while keeping the overall structure sealed. In the embodiment, eight slide rails 13 are fixed in parallel on the outer surface of the air inlet passage 1 from the first annular electromagnet 2 to the air outlet of the air inlet passage 1, and the adjacent slide rails 13 have the same spacing. Eight slide blocks 14 are fixed at the air inlet end of the annular valve 4 of the air inlet passage, which cooperate with the slide rails 13, so that the annular valve 4 of the air inlet passage can slide along the slide rails 13. The sliding fit between the annular valve 4 of the air inlet passage and the air inlet passage 1 can also be in the form of sleeve-axle clearance fit or other forms, which will not be described in detail in the embodiment.

[0025] As shown in Figure 1 and Figure 2 shown, the first annular electromagnet 2 is electrically connected with the first electromagnet DC circuit 21, and the second annular electromagnet 3 is electrically connected with the second electromagnet DC circuit 32, so as to realize independent control of each electromagnet. Please refer to Figure 3 shown, by changing the positive and negative poles of the electromagnet DC circuit, the polarity of the corresponding electromagnet can be changed instantaneously. When the two electromagnet DC circuits pass the same direction current, the opposite ends of the two electromagnets have opposite polarities, and the electromagnets are quickly attracted. When the two electromagnet DC circuits pass the opposite direction current, the opposite ends of the two electromagnets have the same polarity, and the electromagnets are quickly separated.

[0026] As shown in Figure 1 shown, in the embodiment, the outer wall 5 of the combustion chamber is in the form of a barrel structure, the bottom of which is an outwardly convex conical body. In order to reduce the total pressure loss caused by the deflection of high-pressure airflow, the half-cone angle of the conical body is preferably 60°, and the bottom of the barrel structure cooperates with the air outlet of the annular valve of the air inlet passage. The inner wall surface of the outer wall 5 of the combustion chamber surrounds the combustion chamber 51, which is filled with rocket fuel. When the annular valve 4 of the air inlet passage is closed, the aero-engine switches to a rocket engine mode, and the rocket fuel provides power for the rocket engine mode.

[0027] As shown in Figure 1As shown, in this embodiment, the combustion chamber inner passage 7 is formed by the outer wall 5 of the combustion chamber and the inner wall of the turbine-based combustion chamber 6. When the air intake annular valve 4 is opened, the air intake 1 is in communication with the combustion chamber inner passage 7, and the aero-engine is switched to the air-breathing engine mode. In this embodiment, in order to balance the structural strength, fuel storage amount and high-pressure airflow quality in the air-breathing engine mode, the contraction ratio of the exhaust section 12 of the air intake 1 to the combustion chamber inner passage 7 is 0.91.

[0028] Embodiment 2

[0029] This embodiment provides an aero-engine rapid mode switching method using the electromagnetic drive aero-engine rapid mode switching device described in Embodiment 1, comprising the following steps: Please refer to Figure 4 As shown, the step of switching or maintaining the air-breathing engine mode is: the first annular electromagnet 2 and the second annular electromagnet 3 are energized, so that the opposite ends of the first annular electromagnet 2 and the second annular electromagnet 3 have opposite polarities, generating an electromagnetic attraction force, the second annular electromagnet 3 drives the air intake annular valve 4 to move towards the first annular electromagnet 2, and then the first annular electromagnet 2 and the second annular electromagnet 3 are closely attached, the air intake annular valve 4 is opened, the high-pressure airflow enters the combustion chamber inner passage 7 through the air intake 1 and the airflow passage 8, the aero-engine is switched to the air-breathing engine mode, the high-pressure airflow mixes with the fuel in the turbine-based combustion chamber, providing power for the air-breathing engine mode; Please refer to Figure 4 As shown, after the air-breathing engine mode has been switched, the step of switching to the rocket engine mode is: the first annular electromagnet 2 and the second annular electromagnet 3 are energized, so that the opposite ends of the first annular electromagnet 2 and the second annular electromagnet 3 have the same polarity, the second annular electromagnet 3 drives the air intake annular valve 4 to move away from the first annular electromagnet 2, until the air intake annular valve 4 exhaust port is attached to the outer wall 5 of the combustion chamber, the airflow passage 8 is completely closed, the high-pressure airflow is blocked, the aero-engine is switched to the rocket engine mode, and the rocket fuel provides power for the rocket engine mode.

Claims

1. An electromagnetically driven aircraft engine rapid mode switching device, characterized in that: include: An air intake duct (1), a turbine-based combustion chamber (6) fixedly connected to the air intake duct (1); a combustion chamber (51) having a circular cross-section is provided in the turbine-based combustion chamber (6); an internal combustion chamber channel (7) is formed between an outer wall (5) of the combustion chamber and an inner wall of the turbine-based combustion chamber (6); an air flow channel (8) is formed between the outer wall (5) of the combustion chamber and a front inlet of the turbine-based combustion chamber (6); and the air flow channel (8) is communicated with the interior of the air intake duct (1); The air intake duct (1) is provided with a first annular electromagnet (2), a second annular electromagnet (3) and an air intake duct annular valve (4) fixedly connected to the second annular electromagnet (3) on the periphery thereof; the air intake duct annular valve (4) is cylindrical and surrounds the air intake duct (1), and the air intake duct annular valve (4) is inserted from the front end of the turbine-based combustion chamber (6); the air intake duct annular valve (4) moves between a first position and a second position by the attraction or repulsion between the first annular electromagnet (2) and the second annular electromagnet (3); when the air intake duct annular valve (4) is located at the first position, the first annular electromagnet (2) is close to the second annular electromagnet (3) so that the inner channel of the air intake duct (1), the air flow channel (8) and the inner channel (7) of the combustion chamber are connected; when the air intake duct annular valve (4) is located at the second position, the first annular electromagnet (2) is away from the second annular electromagnet (3), and the rear end of the air intake duct annular valve (4) contacts the outer wall (5) of the combustion chamber so that the air flow channel (8) and the inner channel (7) of the combustion chamber are closed.

2. The electromagnetically driven aircraft engine rapid mode switching device according to claim 1, characterized in that: The air inlet duct (1) comprises an air inlet section (11) and an air outlet section (12); the radial cross-section of the air inlet section (11) is an irregular shape, and the radial cross-section of the air outlet section (12) is a circle.

3. The electromagnetically driven aircraft engine rapid mode switching device according to claim 1, characterized in that: A plurality of slide rails (13) are provided on the outer surface of the air inlet duct (1) from the first annular electromagnet (2) to the front end of the turbine-based combustion chamber (6), and a slider (14) is provided inside the air inlet duct annular valve (4) for sliding on the slide rails (13).

4. The electromagnetically driven aircraft engine rapid mode switching device according to claim 1, characterized in that: The first annular electromagnet (2) is electrically connected to the first electromagnet DC circuit (21); and the second annular electromagnet (3) is electrically connected to the second electromagnet DC circuit (31).

5. The electromagnetically driven aircraft engine rapid mode switching device according to claim 1, characterized in that: An annular flange (15) is sleeved on the outer surface of the air inlet duct (1), and the first annular electromagnet (3) is fixedly connected to the annular flange (15).

6. The electromagnetically driven aircraft engine rapid mode switching device according to claim 1, characterized in that: The outer wall (5) of the combustion chamber is a cylindrical structure, and the bottom of the cylindrical structure cooperates with the rear end of the intake duct annular valve (4).

7. The electromagnetically driven aircraft engine rapid mode switching device according to claim 6, characterized in that: The bottom of the barrel structure is an outwardly convex cone, and the semi-cone angle of the cone is 60°.

8. A method for rapid mode switching of an aircraft engine using the electromagnetically driven rapid mode switching device of any one of claims 1 to 7, characterized in that: The following steps are involved: The first annular electromagnet and the second annular electromagnet are energized so that the opposite ends of the first annular electromagnet and the second annular electromagnet have opposite polarities, and the second annular electromagnet drives the annular valve of the air intake duct to move toward the first annular electromagnet, thereby opening the annular valve of the air intake duct and switching the aircraft engine to an air-breathing engine mode. The first annular electromagnet and the second annular electromagnet are energized so that the opposite ends of the first annular electromagnet and the second annular electromagnet have the same polarity. The second annular electromagnet drives the inlet annular valve to move away from the first annular electromagnet until the rear end of the inlet annular valve is in contact with the outer wall of the combustion chamber. The inlet annular valve is closed and the aircraft engine switches to rocket engine mode.

9. The method for rapid mode switching of an aircraft engine according to claim 8, characterized in that: The combustion chamber is filled with rocket fuel, and when the aircraft engine switches to the rocket engine mode, the rocket fuel provides power for the rocket engine mode.

10. The method for rapid mode switching of an aircraft engine according to claim 8, characterized in that: When the aircraft engine switches to the air-breathing engine mode, the high-pressure airflow enters the turbine-based combustion chamber through the air inlet and the airflow channel, and the high-pressure airflow mixes with the fuel in the turbine-based combustion chamber to provide power for the air-breathing engine mode.

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